F-14D. FLIGHT MANUAL (2004)

NAVAIR 01−F14AAD−1

39.1.3.6

Area

39.2.6

MFT and WST Procedures Evaluation

An area is a routine of preflight, flight, or postflight.

An MFT and WST may be used to assist in measuring

the flightcrewmember’s efficiency in the execution of

39.1.3.7

Subarea

normal operating procedures and reaction to emergencies

and malfunctions. In areas not covered by the OFT and WST

A performance subdivision within an area that is

facilities, this may be done by placing the flightcrewmember

covered and evaluated during an evaluation flight.

in an aircraft and administering appropriate questions.

39.1.3.8

Critical Area and Subarea

39.2.7

Grading Instructions

Any area or subarea that covers items of significant

Examination grades shall use a

4.0 scale and be

importance to the overall mission requirements, the marginal

converted to an adjective grade of Qualified or Unqualified.

performance of which would jeopardize safe conduct of the

flight.

39.2.7.1

Open−Book Examination

39.2

GROUND EVALUATION

To obtain a grade of Qualified, an evaluee must obtain

a minimum score of 3.5.

Prior to commencing the flight evaluation, an evaluee

must achieve a minimum grade of Qualified on the

39.2.7.2

Closed−Book Examination

open−book and closed−book examinations. The oral

To obtain a grade of Qualified, an evaluee must obtain

examination is also part of the ground evaluation but may be

a minimum score of 3.3.

conducted as part of the flight evaluation. To assure a degree

of standardization between units, the NATOPS instructors

39.2.7.3

Oral Examination and MFT and WST

may use the bank of questions contained in this chapter in

Procedure Check (If Conducted)

preparing portions of the written examinations.

A grade of Qualified or Unqualified shall be assigned

39.2.1

Open−Book Examination

by the instructor−evaluator.

The open−book examination shall consist of, but not be

39.3

FLIGHT EVALUATION

limited to, the question bank. The purpose of the open−book

examination portion of the written examination is to evaluate

The flight evaluation may be conducted on any routine

the flightcrewmember’s knowledge of appropriate publicaĆ

syllabus flight with the exception of flights launched for

tions and the aircraft.

FCLP and CARQUAL or ECCM training. Emergencies will

not be simulated.

39.2.2

Closed−Book Examination

The number of flights required to complete the flight

The closed−book examination may be taken from, but

evaluation should be kept to a minimum, normally one flight.

shall not be limited to, the question bank and shall include

The areas and subareas to be observed and graded on a flight

questions concerning normal and emergency procedures and

evaluation are outlined in the grading criteria with critical

aircraft limitations. Questions designated critical will be so

areas marked by an asterisk (*). Grades on subareas will be

marked.

assigned in accordance with the grading criteria. Grades on

39.2.3

Oral Examination

subareas shall be combined to arrive at the overall grade for

the flight. If desired, grades of areas shall also be determined

The questions may be taken from this manual and may

in this manner. At the discretion of the squadron or unit

be drawn from the experience of the instructor−evaluator.

commander, the evaluation may be conducted in WST, MFT,

Such questions should be direct and positive and should in no

or COT.

way be based solely on opinion.

39.3.1

Instrument Flight Evaluation

39.2.4

Emergency

Annual NATOPS instrument flight evaluations and the

An aircraft component or system failure or condition

IFR portions of NATOPS flight evaluations, whether conĆ

that requires instantaneous recognition, analysis, and proper

ducted in flight or in an approved simulator, must be

action.

conducted by a NATOPS−qualified pilot or RIO, who is

designated in writing by the unit commanding officer. Such

39.2.5

Malfunction

instrument flight evaluations must be conducted in accorĆ

An aircraft component or system failure or condition

dance with the procedures outlined in the current OPNAĆ

that requires recognition and analysis, but which permits

VINST 3710.

more deliberate action than that required for an emergency.

ORIGINAL

39−2

NAVAIR 01−F14AAD−1

39.4

OPERATIONAL DEPLOYABLE SQUADRONS

Takeoff (pilot)

Pilots and RIOs assigned to operational deployable

Transition to climb schedule.

squadrons will normally be checked as a team, with the flight

evaluation being conducted by the checkcrew flying wing.

39.6.5

Climb and Cruise

RIO commentary will be transmitted on the GCI or CIC

control frequency in use.

Departure (pilot)

39.5

TRAINING AND EVALUATION SQUADRONS

Climb and level−off (pilot)

Units with training or evaluation missions that are

Procedures en route (pilot)

concerned with individual instructor pilot or RIO standardĆ

ization rather than with team standardization may conduct

39.6.6

(*) Approach and Landing

the flight evaluation with the checkcrew−pilot flying wing or

on an individual basis. A pilot may be individually checked

Radar, TACAN (pilot)

with the instructor−evaluator conducting the flight evaluation

from the rear seat. The RIO may be individually checked by

Recovery (pilot).

flying with the instructor−evaluator pilot.

39.6.7

Communications

39.6

FLIGHT EVALUATIONS

Receiving and transmitting procedures (pilot and

The areas and subareas in which pilot and RIOs may be

RIO)

observed and graded for adherence to standardized operating

procedures are outlined in the following paragraphs.

Visual signals (pilot and RIO)

Note

IFF and SIF procedures (RIO).

If desired, units with training missions may

expand the flight evaluation to include evaluation

39.6.8

(*) Emergency and Malfunction

of standardized training methods and techniques.

Procedures.

(*) The IFR portions of the flight evaluation shall be in

In this area, the pilot and RIO will be evaluated only in

accordance with the procedure outlined in the NATOPS

the case of actual emergencies unless evaluation is conducted

Instrument Flight Manual.

in the COT, WST, or OFT.

39.6.1

Mission Planning and Briefing

39.6.9

Postflight Procedures

1. Flight planning (pilot and RIO)

1. Taxi in (pilot)

2. Briefing (pilot and RIO)

2. Shutdown (pilot and RIO)

3. Personal flying equipment (pilot and RIO).

3. Inspection and records (pilot and RIO)

39.6.2

Preflight and Line Operations

4. Flight debriefing (pilot and RIO).

Inasmuch as preflight and line operation procedures

are graded in detail during the ground evaluation, only those

39.6.10

Mission Evaluation

areas observed on the flight check will be graded.

This area includes missions covered in the NATOPS

1. Aircraft acceptance (pilot and RIO)

flight manual, F−14D tactical manual, and naval warfare

publications for which standardized procedures and techĆ

2. Start

niques have been developed.

3. Before−taxiing procedures (pilot).

39.7

RECORD AND REPORTS

39.6.3

Taxi and Runup

A NATOPS evaluation report (OPNAV Form 3710/7)

shall be completed for each evaluation and forwarded to the

39.6.4

(*) Takeoff and Transition

evaluee’s commanding officer only. This report shall be filed

and retained in the individual’s NATOPS jacket. In addition,

1. ATC clearance (pilot)

an entry shall be made in the pilot’s and RIO’s flight

39−3

ORIGINAL

NAVAIR 01−F14AAD−1

logbooks under Qualifications and Achievements" as

To determine the numerical grade for each area and the

follows:

overall grade for the flight, add all the points assigned to the

subareas and divide this sum by the number of subareas

graded. The adjective grade shall then be determined on the

QUALIFICATION

DATE

SIGNATURE

basis of the following scale.

NATOPS

(Date)

(Authenticating

1. 0.0 to 2.19  Unqualified.

EVALUATION

signature)

2. 2.2 to 2.99  Conditionally Qualified.

(Aircraft Model)

(Unit that

3. 3.0 to 4.0  Qualified.

administered

(Crew Position)

evaluation)

Example (add subarea numerical equivalents):

4 + 2 + 4 + 2 + 4

= 3.20 or Qualified

39.7.1

Critique

39.8.2

Final Grade Determination

The critique is the terminal point in the NATOPS

evaluation and will be given by the evaluator−instructor

The final NATOPS evaluation grade shall be the same

administering the check. Preparation for the critique involves

as the grade assigned to the flight evaluation. An evaluee who

processing, reconstructing data collected, and oral presentaĆ

receives an Unqualified on any ground examination or the

tion of the NATOPS evaluation report. Deviations from

flight evaluation shall be placed in an Unqualified status until

standard operating procedures will be covered in detail using

a grade of Conditionally Qualified or Qualified is achieved

all collected data and worksheets as a guide. Upon compleĆ

on a reevaluation.

tion of the critique, the pilot and RIO will receive the

completed copy of the NATOPS evaluation report for

39.9

APPLICABLE PUBLICATIONS

certification and signature. The completed NATOPS evaluaĆ

tion report will then be presented to the unit commanding

The NATOPS flight manual contains the standard

officer.

operations criteria for F−14D aircraft. Publications regarding

environmental procedures peculiar to shorebased and shipĆ

39.8

FLIGHT EVALUATION GRADING CRITERIA

board operations and tactical missions are listed below:

Only those subareas provided or required shall be

1. F−14D tactical manuals

graded. The grades assigned for a subarea shall be deterĆ

mined by comparing the degree of adherence to standard

2. NWPs

operating procedures with adjectival ratings listed below.

Momentary deviations from standard operating procedures

3. NATOPS Air Refueling Manual

should not be considered as unqualifying provided such

4. Air Traffic Control NATOPS Manual

deviations do not jeopardize flight safety and the evaluee

applied prompt corrective action.

5. Local Air Operations Manual

39.8.1

Flight Evaluation Grade Determination

6. Carrier Air Operations Manual.

The following procedure shall be used in determining

the flight evaluation grade. A grade of Unqualified in any

39.10 NATOPS EVALUATION QUESTION BANK

critical area and subarea will result in an overall grade of

The following bank of questions is intended to assist

Unqualified for the flight. Otherwise, flight evaluation (or

the unit NATOPS instructor−evaluator in the preparation of

area) grades shall be determined by assigning the following

ground examinations and to provide an abbreviated study

numerical equivalents to the adjective grade for each subarea

guide. The questions from the bank may be combined with

Only the numerals 0, 2, or 4 will be assigned in subareas. No

locally originated questions in the preparation of ground

interpolation is allowed.

examinations. The closed−book examination will consist of

not less than 25 questions nor more than 75 questions. The

1. Unqualified  0.0

time limit for the closed−book examination is 1 hour and 30

2. Conditionally Qualified  2.0

minutes. The requirements for the open−book examination

are the same as those for the closed−book examination,

3. Qualified  4.0.

except there is no time limit.

ORIGINAL

39−4

NAVAIR 01−F14AAD−1

NATOPS EVALUATION QUESTION BANK

The aircraft weighs approximately ________________ including trapped fuel, oil, gun, pilot and RIO.

The aircraft is __________ in length and has a wing span of __________at 20_ and ______________ in oversweep.

The L INLET and R INLET caution lights indicate __________________.

During normal system operation, the status of AICS ramp control is as follows:

SPEED

Ramp Hydraulic Power

M < 0.35

ON/OFF

Restrained by

M 0.35 to 0.5

ON/OFF

Commanded

M > 0.5

ON/OFF

Programmed as a function of

An AICS failure that causes illumination of an INLET and/or RAMP caution light results in the following:

Speed Range

Ramp Resultant

M < 0.35

M 0.5 to 0.9

M > 0.9

During the AICS portion of OBC, simulated variant flight conditions cycle the ____________________________ through

their full range of operation in about_______ seconds. This exercises the _______________________________________

and ensures ________________________________________.

Operation of the L and R AICS is completely independent.

a. True

b. False

AICS anti−ice is available between ________ Mach and ________ Mach.

With the gear handle down and one or more ramps not in the stow position, the ramp light will be illuminated.

a. True

b. False

10.

The installed thrust of the F110−GE−400 engine is ________ pounds at MRT and ________ pounds at MAX A/B.

11.

In SEC mode, both main engine fuel flow and compressor VSVs are scheduled ____________________________ by the

___________, and fan speed is limited __________by the ____________.

12.

A 3−percent increase in windmill rpm can be achieved by selecting ___________.

13.

Nonemergency selection of the SEC mode should be performed in _________________.

39−5

ORIGINAL

NAVAIR 01−F14AAD−1

14.

The augmenter fan temperature control system regulates five parameters of the engine to provide stall−free operation for

any rate of throttle movement throughout the flight envelope. These parameters are:

15.

The engine electrical control subsystem is powered by an engine gearbox−mounted

(ac

dc)

alternator

that

contains ______________ separate windings, which are:

16.

What are the two power sources for fan speed limiting?

17.

The backup ignition is powered by the aircraft ______________________bus.

18.

Autorelight logic is provided by the ________________________.

19.

What are the throttle interlocks at the military power detent?

20.

Autothrottle may be preflight ground tested on deck either in ______________________ or _______________________.

Indications that a malfunction exists in the autothrottle system are _________________________________________ or

________________________________________.

21.

List oil pressure readings

a. MRT _______________________psi

b. Minimum at IDLE ___________psi

ORIGINAL

39−6

NAVAIR 01−F14AAD−1

22.

An engine stall with no overtemperature will illuminate the appropriate STALL WARNING light in both PRI and SEC

mode.

a. True

b. False

23.

Normal ranges of nozzle position are:

a. IDLE weight on wheels

b. In−flight MRT

c. MIN A/B

d. MAX A/B

24.

What interlocks must be satisfied to activate the nozzle to the full−open position to reduce residual thrust?

25.

Minimum rpm for ground start of the F110−GE−400 engine is _____________________ percent rpm.

26.

Maximum allowable EGT for ground starting the F110−GE−400 engine is ____________________C.

27.

The starting temperature limits are the same for both ground starts and airstarts.

a. True

b. False

28.

At EGT readings of ______________°C ±10, a warning tone is present in the pilot earphones.

29.

At ____________°C, the EGT chevrons begin to flash.

30.

A hot engine should not be started until EGT is below _______________C airborne.

31.

Zero− or negative−g flight is limited to a maximum of ____________________ seconds in military power or less and

________ seconds in afterburner in order not to __________________________________________.

32.

Above __________________ rpm, the MEC should shut off fuel flow to the F110−GE−400 engine.

33.

If the throttle boost system fails, the throttles automatically revert to manual mode, and the throttle mode switch

returns to MAN.

a. True

b. False

34.

What pilot action is required to reset the boost mode of throttle control subsequent to reversion to the manual mode?

35.

______________________________________________________________ is the controlling parameter for the APCS.

39−7

ORIGINAL

NAVAIR 01−F14AAD−1

36.

Autothrottle engagement range is between _______________ and _________________ percent rpm.

37.

If the autothrottles are disengaged by any means, the AUTO THROT light illuminates for a 10−second duration.

a. True

b. False

38.

Engine rpm must be above ___________ percent to supply sufficient power for the main engine ignition system.

39.

When attempting a crossbleed or normal ground start, the ENG CRANK switch will not reengage if the engine is spooling

down and engine rpm is between ____________ and _____________ percent.

40.

During spooldown airstarts, hung starts in the low rpm range

(less than

45 percent) can be assisted with

___________________________. Hung starts in the mid−rpm range

(50 to

60 percent) can be corrected by

___________________________.

41.

If the IGV linkage breaks, the IGVs assume a

_________________ position, which is near normal for

_________________ power settings.

42.

The number of delta Ps to check on each engine during preflight is ________________________.

43.

During an engine ground fire or abnormal start, be sure that the BACK UP IGNITION switch is in the

______________ position.

44.

The L or R FIRE warning lights illuminate when the respective entire sensing loop is heated approximately

___________°F or when any 6−inch section is heated to approximately_______________F.

45.

What procedures should be followed to check oil level if it was not checked within 5 to 30 minutes after shutdown?

46.

During preflight, the oil sight gauge is always a reliable indicator of oil level.

a. True

b. False

47.

The No. __________ bearing receives priority lubrication in the event of a loss of oil.

48.

During cold starts, oil pressure greater than 80 psi should not be exceeded for more than _____________ minute(s).

49.

The electrical source for the oil pressure indicator is _____________.

50.

The OIL PRESS warning light will illuminate when the pressure drops below ______________ psi and extinguishes when

pressure rises above ___________ psi.

51.

The L or R OIL HOT warning light indicates that the supply oil temperature has exceeded __________________ or the

scavenge pump temperature has exceeded _____________.

52.

The INLET ICE caution light illuminates when ____________ or _______________.

53.

In AUTO, pitot probe heat is available only with weight off wheels.

a. True

b. False

ORIGINAL

39−8

NAVAIR 01−F14AAD−1

54.

Which of the following would result in illumination of the FUEL PRESS caution light?

a. Failure of a motive flow pump.

b. Failure of a main fuel pump stage.

55.

Failure of the second stage on the main engine fuel pump will have what effect on engine operation?

56.

Failure of a motive flow fuel pump will have what effect on the engine and fuel system operation?

57.

The loss of an engine−driven boost pump will have what effect on operation of both engines?

58.

Selecting either AFT or FWD with the fuel FEED switch performs what functions in the fuel system?

ąc.

ąe.

ąd.

59.

The L/R FUEL LOW light illuminates with approximately ________________ pounds remaining in the respective

feed group.

60.

Automatic shutoff of wing and drop tank transfer occurs with WING/EXT TRANS switch in either AUTO or ORIDE.

a. True

b. False

61.

The engine boost pump is powered by ____________________________________________________.

62.

To increase bingo fuel specifications, the engine mode select switch may be placed in ________________________

during descents or ____________________________________________________.

63.

The BINGO caution light illuminates when _______________________________.

64.

Is vent tank fuel quantity included in the fuel totalizer on the AFT and L indicator readings?

65.

When should the FEED switch be activated to FWD or AFT?

66.

What medium is used to actuate the feed tank interconnect valve, wing motive flow shut−off valves, and fuel dump valve?

67.

Wing fuel is transferred by:

a. Engine bleed air

b. Motive flow fuel

68.

The fuel thermistors in the outboard section of the wing tanks perform what function?

69.

The fuel thermistors in fuel cell Nos. 2 and 5 perform these functions when either is uncovered:

ąd.

ąe.

ąą

39−9

ORIGINAL

NAVAIR 01−F14AAD−1

70.

All fuel entering the vent tank is vented overboard through the vent mast in the tailhook attachment fairing.

a. True

b. False

71.

Fuel transfer from the external drop tanks is accomplished by __________________.

72.

External fuel transfer can be checked on the deck by __________ or __________.

73.

Fuel dump is prohibited with speedbrakes open and/or afterburner operation.

a. True

b. False

74.

When the fuel dump circuit is activated, wing and external drop tank transfer is automatically initiated.

a. True

b. False

75.

Is it possible to refuel in flight and accomplish total fuel transfer without electrical power or a combined hydraulic system?

If not, why?

76.

On engine start with the generator switch in normal, the generator is automatically excited and the generator control unit

brings it on the line when engine rpm is approximately ____________________ percent.

77.

_________________ stage bleed air is used for IDG oil ground cooling.

78.

If the thermal cutout decouples the drive clutch to either main generator in flight, the IDG may be recoupled (reset) a

maximum of three times.

a. True

b. False

79.

Failure of either ac generator automatically connects the left and right main ac buses to the operative generator.

The cockpit indicator will be a __________________ caution light.

80.

The emergency generator is powered by _____________________.

81.

If the emergency generator switch is in NORM, it will come on the line automatically when ______________________

________________________________________________________.

82.

When operating on the emergency generator, the cockpit lighting available consists of _______________________ and

___________________________.

83.

A single engine−driven pump on the left powers the combined hydraulic system and a single engine−driven pump on the

right powers the flight hydraulic system.

a. True

b. False

ORIGINAL

39−10

NAVAIR 01−F14AAD−1

84.

If the pilot extinguishes the MASTER CAUTION light after a failure of one main hydraulic system, failure of the other

system (will or will not) illuminate the MASTER CAUTION light. Why?

85.

List the requirements for operation of DLC.

86.

With the left engine shut down in flight and

0 percent windmill rpm, the combined hydraulic system can be

87.

With total loss of fluid from either main hydraulic system, the hydraulic transfer pump will ____________________

___________________________________________________________________________________________.

88.

The cockpit handpump will charge the brake accumulator in flight if________________________________________

__________________________________________________.

89.

Loss of all hydraulic fluid from the flight hydraulic system will mean loss of power to the right inlet ramps.

a. True

b. False

90.

With loss of the combined hydraulic system (combined system pressure zero), the main flaps are powered by

___________________ and the auxiliary flaps are __________________________________________________.

91.

With the landing gear emergency blown down, the nosewheel steering and normal brakes will operate after touchdown.

a. True

b. False

92.

The outboard spoiler module uses combined system fluid.

a. True

b. False

93.

Outboard spoilers are inoperative with wing−sweep angles aft of ___________.

94.

The outboard spoiler module thermal cutout is inhibited when ______________________________________________

_______________________________________________.

95.

The ON−OFF flag in the spoiler window of the hydraulic indicator indicates:

a. The outboard spoiler module is energized.

b. The outboard spoiler system is pressurized.

96.

With loss of the combined hydraulic system

(combined system pressure zero) the inboard spoilers will:

_________________________________.

97.

The backup flight control module powers the _____________ and the _____________.

98.

With the backup flight control module switch in AUTO, the module is automatically energized when

_______________________________________________________________________.

99.

The backup flight control module switch has three positions: AUTO, ___________________ and _________________

___________________________.

39−11

ORIGINAL

NAVAIR 01−F14AAD−1

100. The backup flight control module operates in the high−speed mode when ____________________________________

___________________.

101. Operational status of the backup flight control module is indicated in the cockpit by ___________________________

____________________________________________________________________________________________.

102. DLC requires an operable outboard spoiler module.

a. True

b. False

103. Failure of either the combined or flight hydraulic system will have what effect on wing−sweep?

104. On the wing−sweep indicator, there are three position indicators. These show

______________________________

__________________ and ___________________ wing−sweep position.

105. The aircraft is being operated with the wings aft of the forward limit. The wing−sweep control mode indicator reads MAN.

If speed is now increased beyond where the wing−sweep angle and forward limit coincide, the control mode indicator

will read _______________ and the wings will __________________.

106. The most forward wing−sweep angle allowed in bomb mode is __________.

107. The emergency wing−sweep mode is a manual method of positioning the wings. This method incorporates locks every

_____________ from 20_ to 68_ to prevent random wing movement in this mode.

108. Illumination of the WING SWEEP warning light means: _________________________________________________

____________________________________________________________________________________________.

109. Appearance of the W/S warning legend on the MFD means: ______________________________________________

____________________________________________________________________________________________.

110.

Transient failures in the CADC may be reset by: ________________________________________________________

____________________________________________________________________________________________.

111.

The CADC is self−tested in _____________________________.

112.

List the caution, advisory, and warning lights activated by the CADC directly or via the DFCS:

ąe.

ąf.

ąg.

ąh.

113.

When instrument test has been selected on the MASTER TEST panel, the EIG indications after 5 seconds are:

a. RPM

b. EGT

c. FUEL

d. FLOW

ORIGINAL

39−12

NAVAIR 01−F14AAD−1

114.

A degraded mode of EIG operation is indicated by ___________________________.

115.

Maneuver flaps can be lowered at any wing−sweep angle between 20° and ______________________.

116.

The maneuvering flap thumbwheel will lower the main flaps ______________, the auxiliary flaps ____________,

and the slats ____________, Use of the maneuvering devices (does or does not) put more restrictive g limitations on the

aircraft.

117.

What is the meaning of the following (besides CADC failure) ?

a. FLAP caution light

b. REDUCE SPEED warning

(1)Ą

(2)Ą

(3)Ą

118.

Power for emergency extension of the landing gear is supplied by___________________________________________

______________________________________________________________________________________________.

119.

The minimum bottle pressure for accomplishing emergency extension of the landing gear is _____ psi but minimum

preflight bottle pressure is ________ psi at 70_ F (21_ C).

120. Full lateral trim in the direction of stick displacement will reduce maximum spoiler deflection to

_____________ on that side.

121. Full slat asymmetry of 17_ can result in an out−of−control situation at _________ units AOA or greater, even with

55_ of spoilers available.

122. The rudder pedal shaker is armed with main flaps greater than _________________ _ and the ________________

computer operating.

123. With DLC engaged, full−up DLC positions the inboard spoilers at _______________ _ and the horizontal stab trailing

edges ______________.

124. The initial position for spoilers when DLC is engaged is _____________________.

125. The correct positioning for stabilizers when DLC is given a full−down command (from trim) is _________________

trailing edge ___________________.

126. Full rudder throw of ± _________________________ corresponds to ± inches of rudder pedal travel.

127. Control surface authority of the stability augmentation system is:

Pitch ±

Roll ±

Yaw ±

128. The gear handle is down and the three gear position indicators show the gear down, but the transition light is illuminated.

What does this indicate and what action should be taken?

39−13

ORIGINAL

NAVAIR 01−F14AAD−1

129. The ANTI SKID SPOILER BK switch is OFF and the BRAKE light is illuminated. This would indicate:

130. The BRAKE light (ANTI SKID SPOILER BK switch OFF) operates only when the brakes are depressed or the parking

handle is pulled.

a. True

b. False

131. The two procedures for lowering the launch bar are: ________________________ or __________________________.

132. Nosewheel steering cannot be engaged until weight is on wheels.

a. True

b. False

133. With the nosewheel <70°, the nosewheel assumes the position commanded by the rudder pedals when nosewheel steering

is engaged.

a. True

b. False

134. BLEED DUCT light indicates temperatures in excess of ________________ °F between engine and primary heat

exchanger or greater than ___________________°F between primary heat exchanger and the ECS turbine.

135. The ram air door can be opened only if the ___________ or ___________ button is depressed on the ECS control panel.

136. The ram air door automatically closes with selection of L ENG, R ENG, or BOTH ENG on the ECS control panel.

a. True

b. False

137. The ram air door requires ____________ seconds to go full open.

138. The RIO has a low−cockpit−pressure caution light (CABIN PRESS) that illuminates if ______________________

or _______________________.

139. With the OBOGS light on, each flightcrewmember should have _______________ hours of oxygen at 20,000 feet

(8,000 feet cabin altitude).

140. Pulling the emergency oxygen actuator releases gaseous oxygen charged to psi and will provide approximately

a _______________ minute supply.

141. Windshield rain removal is accomplished by blowing 390° F air over the outside of the windshield. If the temperature

sensor detects an overtemperature condition, the WSHLD HOT advisory light will illuminate

and ________________________.

142. Maximum allowable headwind for the open canopy is ____________________ knots.

ORIGINAL

39−14

NAVAIR 01-F14AAD-1

143. When the canopy is jettisoned, the sill locks are released by _______________________________________________.

144. The canopy pneumatic reservoir must be serviced by ground servicing unit.

a. True

b. False

145. The pilot can tell the position of the command ejection lever by ____________________________________________.

146. The RIO can eject both himself and the pilot with EJECT CMD handle set to PILOT.

a. True

b. False

147. The pilot can eject both himself and the RIO with the EJECT CMD handle set to MCO.

a. True

b. False

148. In the event the canopydoes not separate from the aircraft when eitherflightcrewmember hasinitiated ejection, “through

the canopy” ejection will not occur.

a. True

b. False

149. There are ___________________safety pins per ejection seat.

150. Command ejection by either flightcrewmember will eject the RIO in ____ seconds and the pilot ________ seconds later.

151. For a high-altitude ejection, the seat is allowed to free-fall to

_____________________ feet.

152. All exterior lighting controls except for the ____________ light are located on the MASTER LIGHT panel on the pilot

console, and the exterior lights master switch on the outboard throttle.

153. Whenthewingsaresweptaftof__________,the_____________positionlightsare disabledandtheglove positionlights

are operable.

154. When the ANTI-COLLISION light switch is ON, the ________________ position lights flasher switch is disabled.

155. A proper indicator lights test has the MASTER CAUTION light on steady.

a. True

b. False

156. The RIO can monitor SW tones by selection of ___________ position on the ICS panel.

157. The standby attitude indicator is capable of providing reliable attitude information within _______________ for up to

___________ minutes after a complete loss of power.

158. On deck, the allowable error between the pilot and RIO altimeter readings is ____________ feet at field elevation.

39-15

CHANGE 1

NAVAIR 01−F14AAD−1

159. The angle−of−attack indicator is checked during ______________ and the indexer during ____________. Proper indi−

cations are:

a. Indicator 

b. Indexer 

160. In the landing configuration, 15 units AOA is equivalent in airspeed for:

48,000 pound (DLC not engaged) =

KIAS

48,000 pound (DLC engaged/neutral) =

KIAS

50,000 pound (DLC not engaged) =

KIAS

161. With an airspeed indicator failure, list the angle of attack to fly for the following conditions (drag index 8):

a. Catapult

_____________________________________________.

b. Climb (MIL) SL_____________________________________________ to combat ceiling.

c. Cruise at OPT. ALT.________________________________________________________.

d. Endurance a OPT. ALT.______________________________________________________.

162. Stores jettison is controlled by which aircraft system?

163. ACM jettison requires MASTER ARM ON.

a. True

b. False

164. Selective jettison can be completely controlled by either flightcrewmember.

a. True

b. False

165. In the emergency jettison mode, the weight−on−wheels interlock is bypassed.

a. True

b. False

166. Emergency jettison mode will jettison Sidewinders.

a. True

b. False

167. Sidewinder is jettisoned by firing the motor and safing the warhead.

a. True

b. False

ORIGINAL

39−16

NAVAIR 01−F14AAD−1

168. The pretaxi (weight−on−wheels) OBC master test is a complete check of the SMS.

a. True

b. False

169. Selection of any pulse dogfight mode automatically provides stab out aircraft reference.

a. True

b. False

170. The pilot must clear maintenance display prior to running OBC for current test results

a. True

b. False

171. For normal UHF operation with the ARC−182, the AM/FM switch should be in the __________________________

position.

172. With track files established in TWS, the HUD and MFDs provide the pilot complete steering information to the centroid

of the targets.

a. True

b. False

173. The navigation system may be updated by five methods; they are:

ąd.

ąe.

ąą

174. In TACAN BIT, the range and bearing on the HSD and BDHI should indicate _____________________ nm and

__________.

175. The target designator is valid to ± __________ off the nose.

176. With MASTER ARM OFF, the HUD and VDI armament legend will appear with _______________________.

177. To obtain an attack presentation, the air−to−air button must be selected on the PDCP.

a. True

b. False

178. The COOLING AIR light refers to air cooling out of tolerance while the SENSOR COND light indicates liquid cooling

out of tolerance.

a. True

b. False

39−17

ORIGINAL

NAVAIR 01−F14AAD−1

179. The PTID is oriented to ___________________ north, with selection of GND STAB on the PTID mode switch.

180. Which of the following presentations are available to the pilot:

a. IRSTS

b. PS

c. PDS

d. All of the above.

181. A _____________ acronym indicates a failure of the SMS, thus preventing normal separation of stores in any launch

mode.

182. The RADAR COOLING switch in the RIO cockpit controls liquid coolant to __________________.

183. Hostile area altitude is entered in the _______ pseudo file to properly reject altitude line return.

184. Wind is automatically computed by the system in the INS mode.

a. True

b. False

185. A wind of 35 knots and 057_ relative to the duty runway represents a headwind component of ________________

knots and crosswind of _________ knots.

186. A blinking SHOOT cue indicates ______________________________________________________________.

187. Hydraulic power to drive the gun comes from the ___________________________________________ system.

ORIGINAL

39−18

NAVAIR 01−F14AAD−1

CHAPTER 40

Tactical Imaging Set

AN/AVX−3

40.1

AN/AVX−3 TACTICAL IMAGING SET

varies depending on the selected operating mode. Display

brightness is controlled via menu selection.

The Tactical Imaging Set, as installed in the F14D

aircraft, captures, digitizes, and compresses imagery from an

40.1.2

Image Transceiver

external RS 170 video source, then stores and/or transmits it

over a secure communications link. The external video

Image Transceiver functions are controlled by a

source is typically a camera/video system such as the nose

microprocessor. The Image Transceiver also has two

mounted Television Camera System (TCS), Low Altitude

Personal Computer Memories Card International AssociaĆ

Navigation and Targeting System for Night (LANTIRN),

tion (PCMCIA) card slots. The microprocessors executable

Head Up Display (HUD) camera, or other similar systems.

program firmware is stored on an 8 Mbyte flash random

Maximum image capture rate is 4 images/second. The

access memory, called the Program card, in slot 1 (left slot).

Tactical Imaging Set can also receive images transmitted by

Upon power up or reset, the firmware is loaded into 6 Mbytes

other Tactical Imaging Sets or compatible systems (such as

of the Image Transceiver 32 Mbyte image memory. The

ground or base stations). Selected images can be displayed on

remaining

26 Mbytes of image memory is allocated for

the forward

(Video Display Indicator−VDI) and/or aft

storage of uncompressed image frames. The image memory

(Programmable Tactical Information Display − PTID) cockĆ

is volatile, and so stored image frames are lost when power

pit display. The Tactical Imaging Set converts standard

is removed. The RCU sends RS−232 serial commands to

National Television Standards Committee (NTSC) video to

this microprocessor to direct the functions of the Image

allow viewing of still−frame

(single−image) imagery or

Transceiver.

recorded video.

The Image Transceiver accepts an RS 170 format video

The Tactical Imaging Set consists of a Remote Control

input from the VTR (or an external video source via the

Unit

(RCU), Image Transceiver, Video Tape Recorder

VTR), digitizes the video to create an image frame, and

(VTR), Interface Box, and four interconnecting cables (not

passes the image frame to an image buffer for output to the

including connecting aircraft wiring). The RCU mounts in

aircraft cockpit display. The image memory stores selected

the aft cockpit at the inboard front of the right side console.

image frames. Image frames stored in memory can be

The Image Transceiver, VTR, Interface Box, and cables are

randomly accessed for viewing and/or cropping before

mechanically mounted as one unit, called the Naval Airborne

compression. An image compressor (software algorithm)

Video Recorder and Image Transceiver (NAVRIT) Unit,

reduces the size of image frames selected to be stored and

which is mounted in bay 2221−3. Controls and indicators are

routes them to a 4 Mbyte non volatile static random access

shown in Figure 40−1.

memory (SRAM) PCMCIA card, called the Image card, in

slot

0 (right slot) for storage or transmission. The stored

40.1.1

Remote Control Unit (RCU)

image frame includes a clock time code.

The RCU interfaces with the Image Transceiver via an

40.1.3

Video Tape Recorder (VTR)

RS−232 serial bus to enable the Radar Intercept Officer to

remotely control the Image Transceiver functions. ComĆ

The VTR is an airborne video recorder that can record

mand signals are sent from the RCU to the Image TransĆ

and play back up to 2 hours of information on a standard

ceiver, and data is sent from the Image Transceiver to the

Hi 8 format cassette tape. It contains an internal heater to

RCU for display. The RCU display contains 2 lines of 24

prevent condensation. The VTR front panel controls are

green, night vision compatible, alphanumeric characters

disabled; thus all VTR control is remotely performed. RS 422

each. The top line provides status and messages. The bottom

serial command signals are sent from the Image Transceiver

line provides a command menu. The command menu defines

to the VTR, and VTR status data is sent from the VTR to the

the functions of six pushbutton switches located below the

Image Transceiver. Discrete control signals from the aft

display. The command menu, and thus the switch functions,

cockpit Sensor Control Panel are sent to the VTR via the

40−1

ORIGINAL

NAVAIR 01−F14AAD−1

INDEX

NAME

FUNCTION

Display (RCU)

48−character alphanumeric display consisting of 2 rows of

24 characters each. Upper row shows operating status.

Lower row identifies functions of switches.

Switches (RCU)

Six pushbutton switches. Functions are as defined by lower row of

display.

PCMCIA Card Cover Latch

Opens/closes cover for PCMCIA card compartment.

(Image Transceiver)

Image Card Release Button

Releases image card for removal.

(Image Transceiver)

R−W/WP switch

Permits (R−W) or prevents (WP) recording (writing) on image card.

(Reading of image card is always permitted.)

LOCKED latch (Image Card)

Latches and unlatches image card battery compartment.

Program Card Release Button

Releases program card for removal.

(Image Transceiver)

LED 1 lamp (Image Transceiver)

Indicates +28 VDC power is applied to Image Transceiver.

SW1 switch (Interface Box)

Selects video output level.

UP ć nominal 2.2 V (for use with LANTIRN Control Panel installed)

DOWN ć nominal 1.25 V (for use with LANTIRN Control Panel not installed)

REC/STBY/UNTHRD/PLAY/

Non−functional

REW/FF control (VTR)

EMK REC switch (VTR)

Non−functional

PULL OPEN/LOCK latch (VTR)

Opens/closes VTR cassette compartment.

Figure 40−1. Tactical Imaging Set Controls and Indicators (Sheet 2 of 2)

Interface Box. Discrete status signals for certain VTR modes

available commands which are selected using the correĆ

are also sent to the Sensor Control Panel Interface Box.

sponding six pushbutton switches below the display.

40.1.4

Interface Box

1. In bay 2221−3:

a. Ensure Program card is installed in Image TransĆ

The Interface Box provides mechanical mounting for

ceiver slot 1 (left slot).

the VTR and Image Transceiver. Additionally, it provides

electrical connections for dc input power, and connections

b. Ensure formatted Image card is installed in

and switching for digital and video input and output signals.

Image Transceiver slot 0 (right slot).

The Interface Box also modifies the RS 170 video to make

c. Ensure tape cassette is not record protected (red

it compatible with the cockpit displays.

tab should not show) and is installed in VTR.

40.2

OPERATING INSTRUCTIONS

Note

40.2.1

Powerup Sequence

The VTR can record on either Hi 8 or standard

Power up is accomplished using the aft cockpit Sensor

8 mm tape; however, image quality can be subĆ

Control Panel. Once power is applied, the Remote Control

stantially degraded when using standard tape.

Unit

(RCU) controls all functions, although the Sensor

d. Set Interface Box SWl switch as appropriate up

Control Panel can control some Video Tape Recorder (VTR)

if LANTIRN Control Panel is installed; down if

functions. The top line of the RCU display shows status and

LANTIRN Control Panel is not installed.

data. The bottom line of the RCU display shows up to six

40−3

ORIGINAL

NAVAIR 01−F14AAD−1

Set aft cockpit Sensor Control Panel selector to

5. Boot up menu appears.

STBY. RCU displays following sequence:

CS:LOC=###### SND=@@@@@@

PHOTOTELESIS

Ext NiteDay

Where ###### is the local call sign and @@@@@@ is

PHOTOTELESIS

the first entry in the send to call sign directory. (These

entries can be changed using the Settings menus.)

RCU 403

then

6. Press switch corresponding to desired display

brightness level (if current level is satisfactory, do

Waiting ATR startup

not press a switch):

Unit is

EXT−Not used

Waiting for ATR startup

NITE−Nighttime level from Settings menus

After Image Transceiver startup, the following mesĆ

DAY−Daytime level from Settings menus

sage sequence appears:

RCU RESET

7. Press OK switch. Main menu appears at currently

selected brightness level.

PHOTOTELESIS

S=### H=@@@ R=&&& %+:$$$

RCU 403

BrstSnapSet ViewVoc Send

The following message should NOT appear. If it

does appear, there is no Image card in slot 0, or the

Where ### is the number of image frames in the send queue,

Image card installed is not formatted.

@@@ is the number of image frames in the hold queue,

&&& is the number of image frames in the receive queue, %

UNREADABLE IMAGE CARD

is the VTR mode (S = standby, U = unthreaded, P = playback,

flashing R =recording, all others = blank), ± is either a ć or

Fmt

a + indicating tape location is before or after the reset point,

and $$$ is the VTR tape counter time in minutes. When the

Note

system is in data mode (voice communication disabled), the

Pressing OK switch enables process to proceed

&&& field flashes. (Specific switch functions displayed may

without resetting, but results are unpredictable.

vary depending on previous actions; for example, when the

send and hold queues are empty, the SEND switch label is not

If message appears, either:

displayed.).

(1) Install formatted Image card and simultaĆ

Note

neously press OK and FMT switches to reset

If a value in a field is greater than 999, the display

RCU and Image Transceiver. Following message

shows ***.

sequence appears:

40.3

RESETTING RCU AND

RCU RESET

IMAGE TRANSCEIVER

PHOTOTELESIS

The RCU and Image Transceiver may be reset

(rebooted) at any time by simultaneously pressing the two

RCU 403

outermost switches. When this is done, the following

message sequence appears:

ATR RESET

Note

b. (2) Ensure Image card is installed, and press

The hold and compress queues are erased during

FMT switch to format card. Following message

reset.

appears:

Formatting SRAM card

CHANGE 1

40−4

NAVAIR 01−F14AAD−1

ATR RESET

Main

PHOTOTELESIS

Send to Call Sign

Modify Call Sign

RCU−403

Send/Delete Function

Edit Call Sign

Unit is

Waiting for ATR Startup

Capture Rate

RCU RESET

PHOTOTELESIS

Capture Time

RCU−403

Automatic Transmit

CS:LOC=###### SND=@@@@@@

Ext NiteDay

Compression Method

Where ###### is the local call sign and @@@@@@ is the

first entry in the send to call sign directory.

[Wavelets] Compression Ratio

Pressing the OK switch displays the Main menu.

40.4

SETTINGS MENUS

[JPEG] JPEG Quality Factor

The Settings menus are used to modify configuration

parameters for capturing, compressing, transmitting, and

[PTC] PTC Compression Quality

receiving image frames, as well as other system level

functions. The Settings menus are accessed and processed in

sequence from the Main menu (by pressing the SET switch)

PTAC Quickstart

as shown in Figure 40−2.

40.4.1

Settings Menus’ Format

Local Call Sign

The Settings menus follow the general format:

Display Brightness

PARAMETER:

#######

End BackSet Fld PrevNext

Image Dimension

Where ####### (flashing) is the value of the parameter being

set. Switch functions vary somewhat among menus, and are

explained as each menu is described.

Comms Cable ID

Note

EIS Configuration

The FLD, PREV, and NEXT switches are used to

cycle through sets of fields or values. When the

Date and Time

last entry in the set is displayed and the FLD or

NEXT switch is pressed, the first entry in the set

is displayed. When the first entry in the set is disĆ

Format SRAM CardĂă

Waveburst Version Number

played and the PREV switch is pressed, the last

entry in the set is displayed.

Figure 40Ć2.ĄSettings Menus Sequence

40−5

ORIGINAL

NAVAIR 01−F14AAD−1

40.4.2

Send−to−Call−Sign−Menu

PREV − Change currently displayed call sign to previous

call sign in directory

This menu is used to select/deselect the call signs to be

included in the next transmission. It provides access to

NEXT − Change currently displayed call sign to next call

submenus, which are used to maintain the call sign directory.

The menu contains one value field. When selected, the first

call sign in the directory is listed whether or not it is selected

for transmission. The directory can be stepped through using

40.4.4

Edit Call Sign Menu

the NEXT switch, and each entry can be selected or

deselected, as desired. The displays for a call sign value differ

This menu is used to change the name of an existing

slightly depending on whether that value is selected or not

call sign, including a newly added call sign (000000). Each

selected.

character in the call sign is considered a separate value field.

Valid entries for each character are numerals, upper case

letters, and blanks (H, located in sequence between Z and 0).

For a selected call sign value:

Blanks are not permitted within the body of the call sign;

SENDTO CALLSIGN <######>

however, if a call sign has less than 6 characters, trailing

blanks must be added to complete the 6 character call sign.

End Mod Set Yes No Next

Trailing blanks appear on the display only when the call sign

value field is being edited.

For a non−selected call sign value:

MODIFY CALLSIGN ćĂ######Ăāć

SENDTO CALLSIGN ćĂ######Ăāć

Fld PrevNext

End Mod Set Yes No Next

OK − Return to Modify Send to Call Sign menu

END − Return to Main menu

FLD − Select next field in call sign

MOD − Display Modify Call Sign menu

SET − Select next menu in sequence

PREV − Change currently selected call sign character to

previous letter or number

YES − Select call sign

NEXT − Change currently selected call sign character to

NO − Deselect call sign

next letter or number

NEXT − Change currently displayed call sign to next call

40.4.5

Send/Delete Function Menu

This menu is used to toggle the send/delete mode

40.4.3

Modify Call Sign Menu

parameter on or off. In send/delete mode, captured images

This menu is used to add a new call sign to the directory

are deleted as they are sent. With send/delete mode turned

or delete an existing call sign from the directory. It also

off, images are copied to the receive queue as they are sent.

provides access to the Edit Call Sign menu, which is used to

Valid values are YES and NO.

define a newly added call sign.

SEND AND DELETE: ###

MODIFY CALLSIGN ćĂ######Ăāć

End BackSet Next

DoneDel New EditPrevNext

END − Return to Main menu

DONE −Return to Send to Call Sign menu

BACK− Display Send−to Call Sign menu

DEL − Delete the current call sign from the directory

SET − Display Capture Rate menu

and display the next value (if no next value,

default is 000000)

NEXT − Toggle send and delete mode value

NEW − Create new unselected call sign with value of

000000 (if value 000000 already exists, switch

40.4.6

Capture Rate Menu

has no effect)

This menu is used to change the time interval between

image captures in burst mode. Valid values range from 0.1 to

EDIT − Display Edit Call Sign menu

ORIGINAL

40−6

NAVAIR 01−F14AAD−1

999.0. Values are incremented or decremented in 0.1−second

40.4.8

Max Key Time

steps when the value is less than 1 second, and in 1−second

This menu is used to change the duration of time that

steps when the value is greater than 1 second. Incrementing

the Tactical Imaging Set transmits image data to a receiving

once from 999.0 or decrementing once from 0.1 disables

station. This menu allows the maximum transmitting time to

burst mode and enables single shot mode. In this case, the

be set between 10 and 180 seconds, using the change interval

value field indicates SINGLESHOT.

of 1 second. The carrier DCRS stations are programmable

and are set for a Max Transmit Time of 30 seconds. The

Note

Tactical Imaging Set default setting is

30 seconds. The

Tactical Imaging Set will always boot to the last set Max

The capture rate can be set to 0.1 or 0.2 seconds/

image; however, these settings are below the

Transmit Time.

Tactical Imaging Set minimum capture rate

MAX KEY TIME

## SECS

value (fastest capture). If the capture rate is set to

0.1 or 0.2 seconds/image, the Tactical Imaging

End BackSet

PrevNext

Set will capture image frames at its fastest speed,

END − Return to Main menu

which is approximately 0.28 second/image in

capture/hold mode. In capture/send mode, the

BACK− Display Capture Time menu

minimum capture rate value is substantially

higher due to the compression required to transĆ

SET −

Display Automatic Transmit menu

fer image frames to the send queue.

PREV − Decrement currently displayed menu

CAPTURE RATE:

##### SEC

NEXT − Increment currently displayed value

EndąBackSet

PrevNext

END − Return to Main menu

40.4.9

Automatic Transmit Menu

BACK− Display Send/Delete menu

This menu is used to toggle the capture mode

parameter between capture/hold and capture/send modes. In

SET − Display Capture Time menu

capture/hold mode, captured images are placed in the hold

queue. In capture/send mode, captured images are placed in

PREV − Decrement currently displayed

the compress queue for transmission. Valid values are

NEXT − Increment currently displayed value

CAPT&HOLD and CAPT&SEND.

AUTO TRANSMIT:

#########

40.4.7

Capture Time Menu

End BackSet

PrevNext

This menu is used to change the duration of image

END − Return to Main menu

captures in burst mode. Valid values range from 001 to 999.

Values are incremented or decremented in 1−second steps.

BACK− Display Capture Time menu

Incrementing once from 999 or decrementing once from 001

selects continuous capturing. In this case, the value field

SET − Display Compression Method menu

indicates CONTINUOUS.

PREV − Toggle automatic transmission mode value

CAPTURE TIME

### SECS

End BackSet

PrevNext

NEXT − Toggle automatic transmission mode value

END − Return to Main menu

40.4.10 Compression Method Menu

BACK− Display Capture Rate menu

This menu is used to select the compression method

parameter. Valid values are WAVELET, JPEG, and PTC.

SET − Display Max Key Time menu

(PhotoTelesis Classic (PTC) compression is used mainly for

PREV − Decrement currently displayed value

compatibility with older analysis systems.)

NEXT − Increment currently displayed value

40−7

CHANGE 1

NAVAIR 01−F14AAD−1

BACK− Display Compression Method menu

COMPRESS METHOD:

#######

End BackSet

PrevNext

SET − Display PTAC Quick Start menu

END − Return to Main menu

JPEG − JPEG Quality Factor menu

BACK− Display Automatic Transmit menu

FIX − Select fixed ratio parameter entry

SET − Display next menu depending on current comĆ

PREV − Decrement compression ratio value

pression method value:

NEXT− Increment compression ratio value

WAVELET − Compression Ratio menu

PTC − PTC Compression Quality menu

40.4.12 PTAC Quick Start Menu

PREV − Select previous compression method value

This menu is used to toggle the PhotoTelesis Tactical

NEXT − Select next compression method value

(PTAC) quick start parameter on or off. Valid values are OFF

and ON. The parameter indicates whether the PTAC protocol

used during transmission attempts to verify established

40.4.11 Compression Ratio Menu

connections before attempting to transmit images.

This menu is used to select the compression ratio

PTAC QUICK START:

###

parameter when using Wavelet compression. Compression

ratio can be selected from fixed ratios of from 10:1 to 75:1

End BackSet

PrevNext

in increments of 5, or a specific (variable) ratio between 10:1

and 150:1 can be selected by incrementing or decrementing

END − Return to Main menu

the displayed value in steps of 1.

BACK− Display previous menu depending on current

compression method value:

For fixed compression ratio values:

WAVELET − Compression Ratio menu

COMPRESSION RATIO: ### :1

JPEG − JPEG Quality Factor menu

End BackSet Var PrevNext

PTC − PTC Compression Quality menu

END − Return to Main menu

SET − Display Local Call Sign menu

BACK− Display Compression Method menu

NEXT− Toggle quick start on/off value

SET − Display PTAC Quick Start menu

VAR − Select variable ratio parameter entry

40.4.13 Local Call Sign Menu

PREV − Select previous fixed compression ratio value

This menu is used to modify the call sign associated

with the Tactical Imaging Set. Each character in the call sign

NEXT− Select next fixed compression ratio value

is considered a separate value field. Valid entries for each

character are numerals, upper case letters, and blanks (4,

For variable compression ratio values:

located in sequence between Z and

0). Blanks are not

permitted within the body of the call sign; however, if the call

COMPRESSION RATIO: ### : 1

sign has less than 6 characters, trailing blanks must be added

End BackSet Fix PrevNext

to complete the

6 character call sign. Trailing blanks

END − Return to Main menu

CHANGE 1

40−8

NAVAIR 01−F14AAD−1

appear on the display only when the call sign value field is

BACK − Display Brightness menu

being edited.

SET − Display View Communications Cable

LOCAL CALLSIGN ćĂ######Ăāć

Identification menu

End BackSet Fld PrevNext

PREV − Toggle image dimension parameter value

END − Return to Main menu

NEXT − Toggle image dimension parameter value

BACK− Display PTAC Quick Start menu

40.4.16 View Communications Cable Identification

SET − Display Brightness menu

This menu is used to view the type communications

FLD − Select next field in call sign

cable connected to the Image Transceiver. (The cable code

PREV − Change currently selected call sign character to

is hard−wired into the cable connection.) No changes can be

previous letter or number

made from this menu. Normal value is KY−58 DATA.

CABLE: #################

NEXT − Change currently selected call sign character to

next letter or number

End

BackSet

END − Return to Main menu

40.4.14 Display Brightness Menu

BACK− Display Image Dimension menu

This menu is used to set RCU display brightness level

for daytime or nighttime viewing, Valid values are

SET − Display EIS Configuration menu

EXTERNAL (not used), DAY, and NIGHT.

40.4.17 EIS Configuration Menu

ADJUST DISPLAY: ########

This menu is used to change the internal Encryption

End BackSet Dim Brt Next

Interface Subsystem (EIS) configuration file. Viewing file

names and exiting the menu does not change the configuraĆ

END − Return to Main menu

tion file. The file is changed only by loading a new file. EIS

BACK− Display Local Call Sign menu

files are stored on the Program Card. To load a configuration

file, use the PREV and/or NEXT switches such that the name

SET − Display Image Dimension menu

of the desired file is displayed, then press the LOAD switch

to reboot. Normal value is EIS 0001.INI.

DIM − Decrease brightness of display for selected DAY or

NIGHT value

EIS CONFIG:

###########

BRT − Increase brightness of display for selected DAY or

End BackSet LoadPrevNext

NIGHT value

NEXT − Change currently selected brightness value to next

END − Return to Main menu

value

BACK− Display View Communications Cable

Identification menu

40.4.15 Image Dimension menu

SET − Display Date and Time menu

This menu is used to toggle the image dimension

LOAD −Load selected EIS configuration file

parameter value. This parameter defines the image size of

captured images. Valid values are 640 × 480 pixels (full

PREV − Change currently displayed file name to previous

resolution, normal value) and 592 × 440 pixels (center 85%,

file name in directory

used with PTC compression only).

NEXT − Change currently displayed file name to next file

name in directory

IMAGE DIMENSION: #######

End BackSet PrevNext

When the LOAD switch is pressed, the display reads:

END − Return to Main menu

Loading EIS Config

40−9

ORIGINAL

NAVAIR 01−F14AAD−1

When file loading is complete, the RCU and Image

FMT − Format Image card if format value is YES (if

Transceiver are automatically reset (rebooted).

format value is NO, this switch has no effect)

NEXT− Toggle format yes/no value

40.4.18 Date and Time Menus

This menu is used to change the Tactical Imaging Set

Formatting an Image card causes all stored image frames in

date and time. The date and time are expressed in Zulu time

the send and receive queues to be deleted and the display to

format. There are five parts of the date and time parameter.

momentarily read:

Each part is considered a separate value field. Valid entries

for each field are as follows:

Dumping SEND & RECV

When all images are deleted, the display momentarily

FIELD/VALUES

changes to read:

D day of month (dd) / 1 thru 28, 1 thru 29, 1 thru 30,

1 thru 31 (depending on month and year)

Formatting

SRAM card

D hour of day (hh) / 00 thru 23

40.4.20 Waveburst Version Menu

D minute of hour (mm) / 00 thru 59

When formatting is complete, View Version Number menu

D month of year (###) / JAN, FEB, MAR, APR,

is displayed.

MAY, JUN, JUL, AUG, SEP, OCT, NOV, DEC

This menu is used to view the firmware version

D Year (yy) / 00 thru 99 (indicates 1994 thru 2093)

number. No changes can be made from this menu.

DATE/TIME: ddhhmmZ ###yy

WAVEBURST VERSION: #####

End BackSet Fld PrevNext

End

BackSet

END − Return to Main menu

BACK− Display EIS Configuration menu

BACK− Display Format SRAM Card menu

SET − Display Format SRAM Card menu

SET − Display Main menu

FLD − Select next field

40.5

POWER DOWN SEQUENCE

PREV − Change currently selected parameter part field to

previous value in sequence

1. Ensure tape in VTR is in unthreaded condition.

NEXT − Change currently selected parameter part field to

a. On Main menu, observe VTR mode field (%).

next value in sequence

S=### H=@@@ R=&&& %:$$$

40.4.19 Format SRAM Card Menu

BrstSnapSet ViewDataSend

This menu is used to format the Image card (also called

b. If field is any character other than U, sequentially

the Static Random Access Memory (SRAM) card) used to

press VIEW, VTR, and UNTH switches.

store the image frames in the send and receive queues. Valid

values are YES and NO (NO is default).

2. Set aft cockpit Sensor Control Panel selector to

OFF.

FORMAT SRAM CARD: ###

End BackSet Fmt Next

40.6

CAPTURING/COMPRESSING/SAVING/

TRANSMITTING/RECEIVING IMAGES

END − Return to Main menu

40.6.1

Voice and Data Modes

BACK− Display Date and Time menu

The type of communications cable being used is coded

SET − Display View Version Number menu

in the cable wiring, and can be observed on the View

Communications Cable Identification menu. The VOC

switch name appearing on the Main menu indicates the

ORIGINAL

40−10

NAVAIR 01−F14AAD−1

Tactical Imaging Set is in voice mode (data mode selectable).

40.6.2.1.2

Capture/Send Mode

Pressing the VOC switch sets the Tactical Imaging Set to data

1. From the Main menu, press the BRST or SNAP

mode (voice mode selectable), and causes the following

switch. The capture sequence proceeds automatiĆ

menu to appear:

cally with image frames being captured at the speciĆ

S=### H=@@@ R=&&& %:$$$

fied rate for the specified duration (capture time).

BrstSnapSet ViewDatasend

Note

Pressing the DATA switch sets the Tactical Imaging Set to

Due to the processor time required to compress

images, the maximum capture rate (minimum

voice mode (data mode selectable), and the Main menu

time/image) is substantially slower in capture/

appears.

send mode than in capture/hold mode.

S=### H=@@@ R=&&& %:$$$

2. While the image frames are being captured and sent,

BrstSnapSet ViewVoc Send

the following menu sequence appears:

40.6.2

Capturing Images

S=### H=@@@ R=&&&%:$$$

Image frames are captured in either burst mode or snap

Stop

Voc Send

mode. In burst mode, image frames are captured at predeterĆ

mined intervals for a predetermined length of time. In snap

S=### H=@@@ R=&&& %:$$$

(single shot) mode, a single image frame is captured. The

captured image frames are then either transmitted immediĆ

Stop

Abrt

ately (capture/send mode) or stored in the image buffer/hold

3. When the burst duration has expired (image frames

queue (capture/hold mode). All modes and parameters are set

no longer being captured) but image frames are still

using the Settings menu.

being sent, the following menu sequence appears:

40.6.2.1

Capturing Images in Burst Mode

S=### H=@@@ R=&&& %:$$$

BrstSnap

View

Abrt

Note

4. The send queue field (###) increases by 1 as each

If the specified capture rate is SINGLESHOT,

image frame is captured. When the last captured

the BRST switch label does not appear.

image frame is compressed and sent, the send queue

field changes to read 0.

40.6.2.1.1

Capture/Hold Mode

Note

1. From the Main menu, press the BRST or SNAP

Normally, image frames are continuously sent

switch. The capture sequence proceeds automatiĆ

until the send queue is empty; however, at certain

cally with image frames being captured at the speciĆ

capture rate/time settings, transmission may

fied rate for the specified duration (capture time).

cease prior to emptying the send queue, leaving

image frames in the send queue unsent. In these

2. While the image frames are being captured, the

cases, the send queue field is not 0 when the Main

menu appears as follows:

menu appears. Pressing the SEND switch on the

Main Menu transmits the remaining images.

S=### H=@@@ R=&&& %:$$$

Stop

Voc Send

5. When the last image frame in the send queue has

been sent and the next image frame has not yet been

3. The hold queue field (@@@) increases by 1 as each

captured (send and hold queues are empty), the folĆ

image frame is captured.

lowing menu appears:

S= O H=

0 R=&&&

%:$$$

Note

Stop

Voc

If the hold queue is full (typically

188 image

frames), burst mode is discontinued automatically.

6. If it is desired to discontinue sending image frames

before the send queue has been emptied, press the

ABRT switch. The ABRT switch label flashes to

40−11

ORIGINAL

NAVAIR 01−F14AAD−1

indicate the command has been received, and the

40.6.3

Compressing/Saving Images

transmission of image frames ceases. Image capture

Image compression is performed automatically when

continues until the burst duration has expired or the

an image frame is to be transmitted (sent) and/or stored on the

STOP switch is pressed.

Image card in slot 0. The image frame is either placed directly

into the compress queue as it is received (capture/send mode)

7. If it is desired to discontinue capturing image frames

or manually selected and transferred from the hold queue.

before the specified burst duration (capture time)

The transfer from the hold queue can be of all image frames

has expired, press the STOP switch.

(using SAVE switch) or of individual image. Compression

8. If the capture rate is CONTINUOUS, press the

method and parameters are set using the Settings menu.

STOP switch when desired to discontinue capturing

When the image frame has been compressed, it is placed in

image frames.

the send queue for transmission and/or storage with no

further user intervention.

Note

40.6.3.1

Saving Images

D If the send queue is full, burst mode is disconĆ

In capture/hold mode when no call signs are selected

tinued automatically.

for transmission and reception is not occurring, all captured−

but−not−compressed image frames in the hold queue can be

D When the burst duration has expired (image

compressed and stored in the send queue. In this situation, the

frames no longer being captured) and transĆ

following menu appears:

mission has ceased, the Main menu appears.

S=### H=@@@ R=&&& %:$$$

40.6.2.2

Capturing Images in Snap Mode

BrstSnapSet ViewVoc Save

40.6.2.2.1

Capture/Hold Mode

Pressing the SAVE switch transfers all image frames

From the Main menu, press the SNAP switch. The

currently in the hold queue to the compress queue for

capture sequence proceeds automatically with one image

compression and storage in the send queue.

frame being captured. The Main menu remains unchanged,

except that the hold queue field (@@@) increases by 1.

40.6.3.2

Image Card Full

40.6.2.2.2

Capture/Send Mode

If the Image card memory becomes full during

compression, one of the following occurs, depending on

From the Main menu, press the SNAP switch. The

transmit/receive status:

capture sequence proceeds automatically with one image

frame being captured. The following menu appears:

1. If transmission is occurring, all image frames in the

compress queue are transferred to the rear of the

S=### H=@@@ R=&&& %:$$$

hold queue. When the Image card memory becomes

available

(by image frames being deleted), the

BrstSnap

View Abrt

image frames in the hold queue are automatically

1. When the SNAP switch is pressed, the send queue

transferred into the compress queue for compresĆ

field (###) increases by 1. When the last captured

sion and storage on the Image card.

image frame is compressed and sent, the send queue

field changes to read 0. Image frames are continuĆ

2. If reception is occurring, the Tactical Imaging

ously sent until the send queue is empty.

Set must be reset (press the two outer switches

simultaneously).

2. If it is desired to discontinue sending image frames

before the send queue has been emptied, press the

Note

ABRT switch. The ABRT switch label flashes to

indicate the command has been received, image

All image frames in the hold and compress

queues are lost during reset.

capture is discontinued, the transmission of the

image frames ceases, and the Main menu appears.

ORIGINAL

40−12

NAVAIR 01−F14AAD−1

3. If neither transmission nor reception is occurring,

are also transmitted. Image frames in the hold

the following menu appears:

queue are not transmitted. After transmission is

complete, the Main menu appears.

IMAGES NOT SAVED:

###

b. If there are no image frames in the send queue,

Abrt

Cont

all image frames in the hold queue are transferred

to the compress queue, then to the send queue and

Where ### is the number of image frames in the compress

transmitted. After transmission is complete, the

queue including the image frame which is causing the

Main menu appears and the Tactical Imaging Set

full−card condition: In flight, the operator must press the

automatically shifts to voice mode.

ABRT switch to transfer all image frames in the compress

queue to the rear of the hold queue.

c. The S=00% displays to the aircrew the percentĆ

age of transmitted data successfully received by

40.6.4

Transmitting Images

the receiving station.

Image frames which have been captured and comĆ

2. If it is desired to discontinue transmitting image

pressed can be automatically transmitted (capture/send mode

frames before all image frames have been sent,

only) or sent using the SEND switch on the Main menu. The

press the ABRT switch. The ABRT switch label

SEND switch appears when the Tactical Imaging Set is not

flashes to indicate the command has been received,

currently transmitting or receiving image frames, there is at

the transmission of the image frames ceases, and the

least one image frame in the send and/or hold queue, and at

Main menu appears.

least one send−to call sign is selected. New image frames can

be captured during transmission. The PhotoTelesis Tactical

40.6.5

Receiving Images

(PTAC) protocol is used for communication with the external

stations. The PTAC quick start parameter indicates whether

Image reception is normally accomplished after coorĆ

the PTAC protocol attempts to verify established connections

dinating voice communication with the transmitting station.

before attempting to transmit images. The mode (capture/

The Tactical Imaging Set must be in data mode to receive

send or capture/hold), the send−to call signs, and PTAC quick

image frames, and the Main menu is normally active on the

start status are set using the Settings menu. Transmission in

RCU. Image reception cannot occur during transmission, and

capture/send mode is automatic with no user intervention.

the Image card must have sufficient memory available to

Transmission of image frames on command is accomplished

store the received images. Reception is initiated when a

as follows:

transmission to a call sign matching the local call sign is

received. The local call sign is set using the Settings menu.

Note

Once reception is initiated, it proceeds until complete with no

The Tactical Imaging Set transmits image frames

user intervention, although it can be aborted by user

to all selected call signs, but it does so sequenĆ

command. When reception is complete, the Tactical Imaging

tially, that is, it transmits all image frames to the

Set sends an acknowledgement to the sending station, and the

first selected call sign, receives an acknowledgeĆ

Main menu appears on the RCU.

ment (depending on PTAC protocol), then sends

all image frames to the second selected call sign,

1. On the Main menu, press the VOC switch. The

etc. It does not broadcast the image frames to

Tactical Imaging Set shifts into data mode, and

multiple call signs simultaneously.

the following menu appears with the &&& field

flashing to indicate data mode is selected:

1. On the Main menu, press the SEND switch. The

Tactical Imaging Set automatically shifts into data

S=### H=@@@ R=&&& %:$$$

mode, and the following menu appears:

BrstSnapset

ViewDataSend

S=00% H=1 R=1 U+:$$$

2. When reception begins, the following menu appears

BrstSnap Set View Doc

Send

with the &&& field continuing to flash:

a. If there are image frames in the send queue, those

S=### H=@@@ R=&&& %:$$$

image frames are transmitted. Image frames

BrstSnapset

View

Abrt

from the compress queue, which are placed into

the send queue before the send queue is emptied,

40−13

CHANGE 1

NAVAIR 01−F14AAD−1

3. If it is desired to discontinue receiving image frames

The View menu appears as follows:

before all image frames have been received, press

the ABRT switch. The ABRT switch label flashes to

Note

indicate the command has been received, but the

The View menu also provides access to the View

reception of image frames continues until the sendĆ

ing station ceases transmission or times out, at

VTR menu which is used to control the VTR.

which time the following menu appears with the

S=### H=@@@ R=&&& %:$$$

&&& field continuing to flash:

End DumpSendHoldRecvVtr

S=### H=@@@ R=&&& %:$$$

Switch functions are as follows:

BrstSnapSet

ViewDataSend

END − Return to Main menu

Note

DUMP − Display View Dump menu

When the ABRT switch has been pressed, the

SEND − Display View Send menu

Tactical Imaging Set does not send an acknowlĆ

edgement to the sending station.

HOLD − Display View Hold menu

RECV − Display View Receive menu

4. Reception proceeds automatically until complete.

The &&& field is incremented as image frames are

VTR − Display View VTR menu (for VTR

received. When reception is complete, the Main

control)

menu appears with the &&& field continuing to

flash:

Note

If the send, hold, or receive queue is empty, the

S=### H=@@@ R=&&& %:$$$

corresponding switch name label is not disĆ

BrstSnapSet

ViewDataSend

played. If all queues are empty, the DUMP

switch label is also not displayed.

Note

2. The View menu function menus (except for the

The Tactical Imaging Set does not automatically

View Dump menu) follow the general format:

revert to voice mode; therefore, voice mode must

FUNCTION

### OF @@@

be selected to restore voice communications.

End Del MarkCropPrevNext

5. Press the DATA switch. The Tactical Imaging Set

shifts into voice mode, and the Main menu appears:

Where ### is the currently selected image index number and

@@@ is the total number of image frames in the selected

S=### H=@@@ R=&&& %:$$$

queue. An image index number is automatically assigned to

BrstSnapSet ViewVoc Send

an image frame as it is stored, thus the more recent the image

frame, the higher the index number. As image frames are

Alphabetical Index

deleted, index numbers are reassigned to the remaining

image frames so that the index numbers are always sequential

40.7

VIEWING IMAGES

from 1 to the total number of image frames with no gaps.

Images available for viewing are captured image frames

Switch functions vary somewhat among menus, and

in the hold queue, captured, marked, or sent image frames in

are explained as each menu is described.

the send queue, received, sent, or uploaded image frames in

the receive queue, and live/playback VTR output. When no

Note

viewing option is selected, Television Camera System (TCS)

output is displayed on the cockpit display. Image frames in

The PREV and NEXT switches are used to cycle

the hold, send, and/or receive queue can also be deleted. All

through the list of image index numbers in each

functions are accomplished using the View menu.

queue. If the index number displayed is the last

index number in the list, pressing the NEXT

1. Pressing the VIEW switch on the Main menu

switch displays the first index number in the list.

accesses the View menu.

If the index number displayed is the first index

number in the list, pressing the PREV switch disĆ

plays the last index number in the list.

ORIGINAL

40−14

NAVAIR 01−F14AAD−1

3. Viewing and Deleting Image Frames in the Send

updated, and the decompressed next image

Queue

appears on the cockpit display. (If the image

frame deleted is the only one in the send queue,

Compressed image frames in the send queue can be

the Main menu is displayed.)

viewed or deleted using the View Send menu.

Note

a. From the View menu, press the SEND switch.

The View Send menu sequence appears as

Pressing the DEL switch automatically and

follows, and the first image frame in the queue

immediately deletes the image frame. There is no

is decompressed and appears on the cockpit

further prompt to confirm the deletion.

display:

Viewing, Deleting, and Transferring Image Frames

SEND IMAGE

in the Hold Queue.

End Del

PrevNext

Uncompressed image frames in the hold queue can

SEND IMAGE

be viewed or deleted using the View Hold menu.

a. From the View menu, press the HOLD switch.

(Progress bar indicating status of decompression)

The View Hold menu appears as follows, and the

image frame with the displayed index number

SEND IMAGE

1 OF @@@

appears on the cockpit display:

End Del

PrevNext

HOLD IMAGE

1 OF @@@

Switch functions are as follows:

End Del MarkCropPrevNext

END − Return to Main menu

Switch functions are as follows:

DEL − Delete current image frame

END − Return to Main menu

PREV − Display next image frame in queue

DEL − Delete current image

NEXT − Display previous image frame in queue

MARK−Transfer image frame to compress queue

b. Press the PREV or NEXT switch until the desired

CROP − Changes portion of image frame selected

image frame is displayed

PREV − Display previous image frame in queue

The decompressed image appears on the cockpit

display. The number of the image frame displayed

NEXT − Display next image frame in queue

is its position in the queue. This position is based on

the image frames assigned image code (time code for

b. Press the PREV or NEXT switch until the desired

FTI−captured image frames, externally assigned for

image frame is displayed

received and previously loaded image frames). The

queue wraps around so that the image frame selected

The image appears on the cockpit display. The

by pressing the NEXT switch when viewing the last

number of the image frame displayed is its position

image frame in the queue is image frame number 1,

in the queue. This position is based on the image

and the image frame selected by pressing the PREV

frames assigned image code (time code for FTI−capĆ

switch when viewing image frame number 1 is the

tured image frames). The queue wraps around so

last image frame in the queue.

that the image frame selected by pressing the NEXT

switch when viewing the last image frame in the

c. If the image frame is to be deleted, press the DEL

queue is image frame number 1, and the image

switch. The image frame is deleted, the index

frame selected by pressing the PREV switch when

number of the next image frame in the queue is

viewing image frame number 1 is the last image

displayed, the total number of image frames is

frame in the queue.

40−15

ORIGINAL

NAVAIR 01−F14AAD−1

c. If the selected image frame is to be deleted, press

a. From the View menu, press the RECV switch.

the DEL switch

The View Receive menu sequence appears as folĆ

lows, and the image frame with the displayed

The image frame is deleted, the index number of

index number is decompressed and appears on

the next image frame in the queue is displayed, the

the cockpit display:

total number of image frames is updated, and

the next image appears on the cockpit display.

RECV IMAGE

(If the image frame deleted is the only one in the

End Del Mark

PrevNext

hold queue, the Main menu is displayed.)

SEND IMAGE

Note

Pressing the DEL switch automatically and

(Progress bar indicating status of decompression)

immediately deletes the image frame. There

is no further prompt to confirm the deletion.

RECV IMAGE

1 OF

@@@

d. If the selected image frame is to be transferred to

End Del Mark

PrevNext

the compress queue for storage and/or sending:

Switch functions are as follows:

(1) Select the portion of the image frame to be

transferred by pressing the CROP switch.

END − Return to Main menu

The cropping window over the image on the

DEL − Delete current image

cockpit display is initially set to select the

entire image (100%). Pressing the CROP

MARK − Transfer image frame to send queue

switch successively reduces the selected

portion to the center 75%, 50%, or 25% of

PREV − Display image with previous index

the image, as shown by the cropping window

number

on the cockpit display. Pressing the CROP

NEXT − Display image with next index number

switch when 25% is selected restores the

100% selection.

b. Press the PREV or NEXT switch until the desired

Note

image frame is displayed

The center of the cropping window is fixed at

The decompressed image appears on the cockpit

the center of the image.

display. The number of the image frame displayed is

its position in the queue. This position is based on

(2) When the desired image frame portion has

the image frames assigned image code (time code

been selected, press the MARK switch to

for FTI−captured image frames, externally assigned

transfer the selected portion to the compress

for received and previously loaded image frames).

queue. (The portion of the image frame outĆ

The queue wraps around so that the image frame

side the cropping window is discarded.) The

selected by pressing the NEXT switch when viewĆ

image frame is automatically deleted from

ing the last image frame in the queue is image frame

the hold queue, the total number of images

number 1, and the image frame selected by pressing

in the hold queue is updated, the next image

the PREV switch when viewing image frame numĆ

frame in the hold queue is selected, and the

ber 1 is the last image frame in the queue.

selected image appears on the cockpit disĆ

play. (If the image frame transferred is the

only one in the hold queue, the Main menu

c. If the image frame is to be deleted, press the DEL

is displayed.)

switch

The image frame is deleted, the index number

Viewing, Deleting, and Sending Image Frames in

of the next image frame in the queue is displayed,

the Receive Queue

the total number of image frames is updated, and

Compressed image frames in the receive queue can

the decompressed next image appears on the

be viewed, sent, or deleted using the View Receive

cockpit display.

(If the image frame deleted is

menu.

ORIGINAL

40−16

NAVAIR 01−F14AAD−1

the only one in the receive queue, the Main menu is

40.8

CONTROLLING VTR FUNCTIONS

displayed.)

The VTR can be controlled from either the RCU or the

Note

aft cockpit Sensor Control Panel, with the Sensor Control

Panel taking precedence. When the Sensor Control Panel

Pressing the DEL switch automatically and

RECORD switch is set to OFF, power is removed from the

immediately deletes the image frame. There

Tactical Imaging Set, and the VTR tape is unthreaded. When

is no further prompt to confirm the deletion.

the Sensor Control Panel RECORD switch is set to RECD,

the VTR is commanded to record. When the Sensor Control

d. If the selected image frame is to be sent

Panel is set to STBY

(normal situation), the VTR is

(forwarded), press the MARK switch to copy

commanded to perform the function set by the RCU. In either

the selected image frame to the send queue.

case, the Sensor Control Panel indicator lights indicate

The image frame is retained in the receive queue.

standby, end of tape (EOT), or unthreaded VTR status, as

While the image remains in the send queue, it cannot be

applicable. In practice, it is recommended that if the Sensor

marked again for transmission.

Control Panel is used to control the VTR record function, the

RCU have STBY selected. If the RCU is used to control the

6. Deleting All Image Frames in One or More Queues

VTR functions, the Sensor Control Panel selector must be set

to STBY.

The send, hold, and/or receive queues can be emptied

of image frames using the View Dump menu.

1. VTR control functions are part of the Tactical

a. From the View menu, press the DUMP switch

Imaging Set view functions

The View Dump menu appears as follows:

The View menu is accessed by pressing the

VIEW switch on the Main menu. The View menu

SELECT IMAGES TO DUMP

appears as follows:

End

SendHoldRecvAll

S=### H=@@@ R=&&& %:$$$

Switch functions are as follows:

End DumpSnd Hld Rcv Vtr

END − Return to Main menu

There are two levels of recorder functions menus;

SEND − Delete all image frames in the send

the Record Level menu (indicated by the presence

queue

of the REC switch name), and the Play Level menu

(indicated by the presence of the PLAY switch

HOLD− Delete all image frames in the hold

name).

queue

RECV− Delete all image frames in the receive

a. Record Level Menu

queue

To access the Record Level recorder functions

ALL − Delete all image frames in all queues

menu, press the VIEW switch on the Main menu,

then press the VTR switch on the View menu. The

Note

Record Level menu appears on the RCU.

If the send, hold, or receive queue is empty, the

$$$$$$$$$$$$$$ +hh:mm:ss

corresponding switch name position is blank.

End Set StbyRec UnthRset

b. Press the switch corresponding to the desired

queue(s) from which image frames are to be

Where $$$$$$$$$$$$$$ is the current VTR funcĆ

deleted

tion, ± is either a − or a + indicating tape location is

All image frames in the selected queue(s) are

before (−) or after (+) the tape counter reset point,

deleted, and the Main menu is displayed.

and hh:mm:ss is the tape counter time since reset in

hours, minutes, and seconds.

Note

VTR function indications are as follows:

Pressing the SEND, HOLD, RECV, or ALL

BOT − Tape has been rewound to beginning

switch automatically and immediately deletes all

image frames in the selected queue(s). There is

EOT − Tape has been forwarded to end

no further prompt to confirm the deletion.

40−17

ORIGINAL

NAVAIR 01−F14AAD−1

F−FWD − VTR is fast−forwarding the tape

Field definitions and VTR function indications are

the same as for the Record Level menu. Switch

PLAY − VTR is playing back a tape

functions are as follows:

RECORD − VTR is recording video

END − Return to Main menu

REWIND − VTR is rewinding the tape

BACK − Display Record Level menu

SCAN FORWARD − VTR is scanning the tape in

the forward direction

STIL − Set VTR to pause (freeze frame) function

SCAN REVERSE − VTR is scanning the tape in

PLAY − Set VTR to play function

the reverse direction

REW − Set VTR to rewind function

STANDBY − Tape is stopped and threaded on

FF − Set VTR to fast forward function

VTR tape heads; VTR is not recording or

playing back video

STILL −Tape is stopped and threaded on VTR

40.8.1

Function Operations

tape heads, and VTR is outputting single

video image (pause or freeze frame)

Changing Between Record Level and Play Level

Menus

UNTHREAD − Tape is unthreaded from VTR

tape heads

a. To change to the Play Level menu from the

Record Level menu, press the SET switch.

Note

b. To change to the Record Level menu from the

Play Level menu, press the BACK switch.

If the VTR function is RECORD, the RSET

switch is replaced by an EMK switch.

Recording Video

Switch functions are as follows:

On the Record Level menu, press the REC

switch. The VTR terminates whatever function it,

END − Return to Main menu

was performing and shifts into record mode. Tape

moves forward (unless it is at end of tape), and video

SET − Display Play Level menu

is recorded.

STBY − Set VTR to standby function

Event Marking

REC − Set VTR to record function

On the Record Level menu while recording,

press the EMK switch. An event mark signal

UNTH − Set VTR to unthread function

is recorded on the tape when the EMK switch is

pressed. Any number of event marks can be placed

RSET − Reset tape counter to +00:00:00

on the tape.

EMK − Place event mark signal on tape (during

Resetting Tape Counter

recording only)

On the Record Level menu while performing any

function except recording, press the RSET switch.

b. Play Level Menu

The tape counter is reset to +00:00:00.

To access the Play Level recorder functions

Playing Back Video

menu, press the SET switch on the Record Level

menu. The Play Level menu appears on the RCU.

On the Play Level menu, press the PLAY switch.

The VTR terminates whatever function it was

$$$$$$$$$$$$$$ +hh:mm:ss

performing and shifts into play mode. Tape moves

End BackStilPlay REW FF

forward (unless it is at end of tape), and video is

reproduced (played back) from the tape.

ORIGINAL

40−18

NAVAIR 01−F14AAD−1

Pausing (Freeze Framing)

11. Stopping Tape

On the Play Level menu while in play function,

On the Record Level menu, press the STBY

press the STIL switch. The tape stops moving, and

switch. The tape stops moving, but remains

the VTR outputs the image recorded at that point on

threaded Video is not reproduced (played back)

the tape. If this function is active for 5 consecutive

from the tape. If this function is active for

minutes, the VTR automatically shifts into unthread

consecutive minutes, the VTR automatically moves

function to protect the tape.

the tape forward for 0.5 seconds to protect the tape.

Scanning Forward

12. Unthreading Tape

On the Play Level menu, press the PLAY switch,

On the Record Level menu, press the UNTH

then the FF switch. The VTR terminates whatever

switch. The tape stops moving, and the tape is

function it was performing and shifts into play, then

unthreaded from the VTR tape heads. Video is not

scan forward mode. Tape moves forward (unless it

reproduced (played back) from the tape. (Tape must

is at end of tape) at 7 times normal playback speed,

be unthreaded before the tape cassette can be

and video is reproduced (played back) from the

removed from the VTR).

tape. If an event mark is encountered while scanning

forward, VTR shifts into play function.

40.9

ERROR MESSAGES

If a problem with the VTR exists, an error message

Scanning in Reverse

appears in the VTR function indication field of the Record

On the Play Level menu, press the PLAY switch,

Level or Play Level menu, whichever is active. Possible error

then the REW switch. The VTR terminates whatĆ

messages include:

ever function it was performing and shifts into play,

then scan reverse mode. Tape moves backward

40.9.1

DEW

(unless it is at beginning of tape) at 7 times normal

playback speed, and video is reproduced (played

Condensation has occurred in the VTR (tape motion

back) from the tape. If an event mark is encountered

and unthreading is inhibited until condensation evaporates).

while scanning in reverse, VTR shifts into play

function.

40.9.2

COMMS ERROR

An error, such as a framing or parity error, has occurred

Fast−Forwarding

in an RS−422 command to the VTR

On the Play Level menu when not in play

function, press the FF switch, or on the Play Level

40.9.3

INTERNAL ERROR

menu when in play function, press the FF switch

A problem inside the VTR (e.g., with the tape path,

twice. The VTR terminates whatever function it was

heads, or motors) exists.

performing and shifts into fast forward mode. Tape

moves forward (unless it is at end of tape) at high

40.9.4

COMMAND ERROR

speed. Video is not reproduced (played back) from

the tape.

An impossible function (e.g., playing or recording with

no tape installed, playing or recording when tape is at its end,

10. Rewinding

recording on write−protected tape) has been commanded.

On the Play Level menu when not in play

function, press the REW switch, or on the Play

Level menu when in play function, press the REW

switch twice. The VTR terminates whatever funcĆ

tion it was performing and shifts into rewind mode.

Tape moves backward (unless it is at beginning of

tape) at high speed. Video is not reproduced (played

back) from the tape.

40−19 (Reverse Blank)

ORIGINAL

ąNAVAIR 01−F14AAD−1

INDEX

Page

No.

APG−71 PM acronym

14−28

Applicable publications

39−4

Approach:

Abnormal Start

12−1

Lights

2−251

Aborted takeoff

13−1

Pilot functional checklight procedures

10−27

Checklist

13−1

Accelerated Departures

11−14

RIO functional checkflight procedures

10−31

Acceleration limits

4−5

Approach power compensator:

Performance

17−3

Aft hung ordnance landings

15−16

Technique

8−9

Aft wing−sweep landings

11−27, 15−11

Area around aircraft, inspection of

7−1

After landing, cold−weather operations

18−6

Arrested landing and exit from landing area

8−10

Afterburner:

Night

8−13

Fuel control

2−13, 2−23

Arresting hook:

Ignition

2−32

Emergency down

15−21

Air inlet control system

2−1

System

2−145

Malfunctions

14−16

Ascent checklist

7−23

Air−conditioning, cockpit

2−151

Asymmetric−thrust−induced departures

11−14

Aircraft

Part I

Asymmetric thrust flight characteristics

11−22

Fuel system

2−40

In combat and cruise configuration

11−4

Lighting during night formation flight

9−4

Asymmetric wing sweep

11−31, 15−11

Self−test

Chapter 38

Flight characteristics

11−32

Subsystems

17−2

Audio warning signals

19−5

Aircrew coordination

37−1

Authorized stores loading

4−21

Single−engine failure field/catapult launch

Automatic carrier landing system

17−1

waveoff

13−2

Beacon augmentor

17−2

Airspeed:

Displays

17−3

Limitations

4−1

Procedures

17−10

Subsonic

11−5

Automatic fuel electrical controls

2−59

Airstart(s)

2−32, 2−34, 14−7

Automatic landing system (AN/SPN−42)

17−8

Envelope

4−1

External

2−32

Autopilot

2−125

Emergency disengage

2−126

Twenty thousand feet

10−20

Light

14−48

All−weather operations

Part VI

Limits

4−1

AN/APN−194(V) radar altimeter system

2−250

Auxiliary brake

2−140

AN/APX−76 identification friend or

Auxiliary canopy open control

2−77

foe interrogator

21−6

Auxiliary flap failure

15−10

AN/APX−100 identification transponder

21−1

Avionic bit operation

38−10

AN/ARC−182 V/UHF radio

19−7

AN/ARN−118 tactical air navigation system

20−8

AN/ASN−139 inertial navigation set

20−1

AN/ASW−27C data link

20−11

AN/AVX−3 Tactical imaging set

40−1

AN/URC−107 joint tactical information

Backup flight control system

2−73

distribution system

20−8, 20−12

Backup flight module malfunction

14−35

AN/USN−2(V) standard attitude heading

Backup ignition

2−32

reference system

20−5

Backup oxygen supply servicing data

3−8

Angle−of−attack:

Backup oxygen system

2−159

Limits

4−5

Banner towing

9−4

System

2−251

Restrictions

4−20

Antennas, communications

19−1

Barricade arrestment

15−18

Anti−ice, engine

2−27

Barricade engagement limits

4−18

Antiskid

2−138

Bearing distance heading indicator

20−11

Index−1

ORIGINAL

NAVAIR 01−F14AAD−1

Page

No.

Before leaving aircraft, cold−weather operations

18−6

Center of gravity:

Binding/jammed flight controls on deck

12−4

Aft locations, flight characteristics with

11−38

Bingo fuel

8−9

Position limits

4−18

Bleed air, engine

2−27

Checkflight procedures

10−1

Block Numbers

1−2

Checkout, on−board

38−3

Blown tire:

Clean and symmetric stores loading

4−13

During takeoff

13−3

Climb:

Landing

15−10

Flight evaluation

39−3

Boarding ladder

2−283

Pilot functional checkflight procedures

10−2

Bolter

8−12

RIO functional checkflight procedures

10−27

Technique

8−9

Climb to thirty−five thousand feet

Both combined and flight pressure zero

14−33

Pilot functional checkflight procedures

10−20

Brake:

RIO functional checkflight procedures

10−29

Characteristics

2−138

Closed−book examination, NATOPS

39−2

Failure at taxi speed

12−4

Cockpit

1−1

BRAKES warning light

2−140

Air−conditioning

2−151

Break formation

9−3

Overpressurization on deck

14−28

Briefing:

Temperature control malfunction

14−28

Carrier−based procedures

8−1

Cold−weather operations

18−4

Mission

39−3

Combined dynamic and viscous hydroplaning

18−3

Preflight

6−1

Combined pressure approximately

B/U OXY LOW light

14−29, 14−30

2,400 to 2,600 psi

14−31

Built−in test:

Combined pressure zero

14−32

Description

38−7

Command ejection lever

2−263

Engine instrument group

2−37

Communications

Chapter 19

And associated equipment

19−1

Antenna

19−1

Emergency procedures

14−1

CABIN PRESS light

14−28

Failure

14−1

CADC light

14−47

Flight evaluation

39−3

Canopy:

In−flight visual

19−27

Control, normal

2−77

Communications−navigation equipment

Open control, auxiliary

2−77

and procedures

Part VII

System

2−254

Compressor stall

14−5

Carrier:

Controllability check

14−35

Landing pattern (VFR)

8−7

Controller processor signal unit

22−2

Preflight

8−1

Converter interface unit

20−6

Carrier−based procedures

Chapter 8

COOLING AIR light

14−27

Carrier−controlled approaches

8−10

Cooling, electronic equipment

2−152

Catapult:

Cooperative support software

38−40

Launch

8−5, 8−12

Coordination, aircrew

37−1

System, nosegear

2−143

Coupling, inertia

11−14

Trim requirements

8−5

Crank, engine

2−32

Catapult abort procedures

Critique

39−4

Day

8−6

Cross−control−induced departures

11−13

Night

8−13

Crossbleed start

2−34

Catapult hookup

Crosswind limits

4−1

Day

8−4

Cruise:

Night

8−12

And combat flight characteristics with aft cg

11−38

Caution legends, multifunction display engine

2−38

Flight evaluation

39−3

Caution light, OIL HOT

2−35

Formation

9−3

Ceiling/visibility requirements

5−2

Cursor controls

2−174

CHANGE 1

Index−2

NAVAIR 01−F14AAD−1

Page

No.

Electrical fire

14−22

Electrical operation:

Danger areas, ground handling

3−8

Degraded

2−62

Data:

Normal

2−59

Display system

22−2

Electrical power:

Entry unit

2−242

Distribution

2−61

Link

17−2

Supply system

2−59

Deck−launched intercept procedures

7−35

Electronic equipment cooling

2−152

Definitions, NATOPS evaluation

39−1

Electronic nomenclature

1−5

Defueling

2−56

Emergency entrance

12−2

Degraded approach configuration

11−27

Emergency gear extension

2−77, 2−136

Degraded electrical operation

2−62

Emergency jettison

14−2

Departure:

Emergency oxygen supply

2−160

From controlled flight

11−10

Emergency procedures

39−3, Part V

Recovery

11−15

Engaging speeds

15−18

Spin

14−49

Engine

Chapter 1, 2−9

Descent

7−23

Anti−ice

2−27

RIO functional checkflight procedures

10−29

Bleed air

2−27

Diamond four−plane formation

9−3

Compartment ventilation

2−30

Digital data system

22−26

Control, main

2−21

Digital flight control system

2−109, 17−2

Crank

2−32

Digital flight control system test

2−129

Emergencies

14−5

Dihedral effect

11−6

Feed

2−43

Direct lift control

2−109

Fire on the deck

12−1

Directional (yaw) control

11−1

Fuel boost pump

2−21

Directional stability

11−6

Fuel system

2−21

Directives, technical

1−2

Ignition system

2−30

Display system, TARPS

22−2

Instruments

2−35

Displays

2−161

Limit

4−1

Subsystem

20−6

Monitor display format

2−37

Distance measuring equipment fix

8−10

Overspeed

14−12

Double generator failure

14−20a

Overtemperature warning

2−38

Double transformer−rectifier failure

14−22

RPM indicator

2−35

Dual hydraulic failures backup flight

Runup, pilot functional checkflight procedures . . 10−13

control module flight characteristics

11−33

Stall warning

2−38

Dual−engine landing, one or both engines in

Stalls

11−5

secondary mode

15−1

START VALVE light

14−12

Dump, fuel

2−55

Starting system

2−32

Dutch roll

11−3

Transfer to SEC mode

14−12

Dynamic hydroplaning

18−2

Engine instrument

Dynamic longitudinal response characteristics

11−2

Group built−in test

2−37

Group self−test

2−37

Engine oil:

Pressure indicator

2−37

Ejection:

Servicing data

3−4

Envelope

16−1

System

2−34

Preparation

16−5

Engine start:

System

2−256a

Cold−weather operations

18−5

Ejection initiation

2−263, 16−6

Pilot

7−11

Ejection seat

2−258

RIO

7−30

Inspection

7−6

Environmental control system

2−148

Operation limits

4−1

Leak detection

2−29

Electrical controls, automatic fuel

2−59

Malfunctions/failures

14−25

Electrical failure

14−20

Equipment:

Total

14−24

Circuit breakers, TARPS

22−2

Index−3

CHANGE 2

NAVAIR 01−F14AAD−1

Page

No.

Communications and associated

19−1

General

11−2

Miscellaneous

2−283

High angle of attack

11−6

Evaluation:

Single engine

14−11

Flight

39−3

With aft cg locations

11−38

NATOPS

Chapter 39

Flight control systems

2−97

Exhaust gas temperature indicator

2−35

Backup

2−73

Exhaust nozzle:

Failures or malfunctions

14−35

Failed (no nozzle response to throttle

Flight evaluation(s)

39−3

movement)

14−15

Grade determination

39−4

Position indicator

2−37

Grading criteria

39−4

Variable

2−16

Flight pressure:

Exterior inspection

7−1

Approximately 2,400 to 2,600 psi

14−31

Exterior lights

2−265

Zero

14−33

External airstart

2−32

Flightcrew:

External baggage container

2−284

Attention signals

14−1

External stores limits

4−19

Coordination

Chapter 37

Extreme weather operations

Chapter 18

Flight training syllabus

5−2

Forced landing

15−21

Foreign object damage and leak inspection

7−1

Formation flight

9−2, 37−4

Aircrew coordination

37−1

Takeoff

7−22

Fatigue engine monitoring system

2−18

Formats

2−176

Field arresting gear

15−17

Fuel:

Field arrestments

15−17

Boost pump, engine

2−21

Field carrier landing practice

7−36

Dump

2−55

Fifteen thousand foot checks:

Flow indicator

2−37

Pilot functional checkflight procedures

10−16

Leak

14−19

RIO functional checkflight procedures

10−28

Management system operational check

9−7

Final grade determination

39−4

Pressure caution lights/Low Fuel

Fire:

Pressure Warning Tone

14−18

Detection system

2−39

Pump

2−21

Electrical

14−22

Quantity balancing

2−54

In Flight

14−4

Quantity system

2−42

Light in flight

14−4

Tankage

2−42

Flameout

11−5

Fuel system:

Flap and slat

2−89

Aircraft

2−40

Asymmetry

14−46

Engine

2−21

Landing emergencies

15−10

Malfunctions

14−18

Transition limits, takeoff and landing

4−13

Fuel transfer

2−50

FLAP light

14−45

During single−engine operation

2−54

Flap(s):

Failures

14−19

Maneuvering

11−7

Fueling

2−56

Up takeoff

7−21

Functional checkflight procedures

Chapter 10

Flat spin

11−20

Aircrew coordination

37−1

Flight:

Pilot

10−2

And combined systems

2−69

RIO

10−27

Equipment requirements, flight crewmember

5−5

Instruments

2−248

Preparation

Chapter 6

Procedures, banner towing

9−4

Training syllabus

5−2

Flight characteristics

Chapter 11; Part IV

Gear extension, emergency

2−77

Asymmetric thrust

11−22

Generator failure

14−20

Dual hydraulic failures backup flight

Grade determination, flight evaluation

39−4

control module

11−33

Grading criteria, flight evaluation

39−4

CHANGE 2

Index−4

NAVAIR 01−F14AAD−1

Page

No.

Grading instructions, ground evaluation

39−2

In−flight emergencies

Chapter 14

Gross weight limits, takeoff/launch/landing

4−18

In−flight reconnaissance system check, RIO

7−32

Ground clearances, towing

3−15

In−flight refueling

2−57, 9−1

Ground egress without parachute and

In−flight visual communications

19−27

survival kit

12−2

Indicator(s):

Ground emergencies

Chapter 12

Engine oil pressure

2−37

Ground evaluation, NATOPS

39−2

Engine RPM

2−35

Ground handling

3−8

Exhaust gas temperature

2−35

Signals

19−27

Exhaust nozzle position

2−37

Ground operations limits

4−1

Fuel flow

2−37

Ground procedures, banner towing

9−4

Lights

2−269

Ground refueling

3−1

Multistatus

2−170

Ground roll braking failures

15−21

Oil pressure

2−35

Ground safety devices and covers, inspection of

7−1

Indoctrination

Chapter 5

Ground training requirements/syllabus

5−1

Inertial navigation set (AN/ASN−139)

20−1

Gun:

INLET ICE light

14−17

Burst limits

4−19

Inspection:

Gas purging

2−154

Areas

7−2

Limits

4−19

Exterior

7−1

Instrument:

Engine

2−35

Flight evaluation

39−2

Procedures

Chapter 17

Handling

Chapter 3

Instrument landing system:

Heads−up display

2−169

AN/ARA−63

17−5

Heads−up display symbology

22−13

AN/SPN−41

17−8

High angle of attack flight characteristics

11−6

Displays

17−3

High energy ignition, main

2−30

Integrated drive generator oil servicing data

3−4

High speed dash (thirty−five thousand feet):

Integrated trim system

2−97

Pilot functional checkflight procedures

10−21

Intercommunications

19−1

RIO functional checkflight procedures

10−29

Interference, mutual

19−1

Hold phase

8−10

Interim AIM−7 as ballast

4−21

Holdback fitting

2−145

Interior inspection:

Horizontal tail authority figure

14−42

Pilot

7−8

Hot refueling

2−58

RIO

7−28

Procedures

7−34

Interior lights

2−268

Hot switch procedures

7−36

Internal tank pressurization and vent

2−56

Hot−weather and desert operations

18−6

Inverted departure/spin

14−50

Hydraulic power:

Inverted spin

11−21

Distribution

2−72

Inverted stall/departure

11−20

Supply systems

2−69

Hydraulic system:

Malfunctions

14−31

Servicing data

3−4

Hydroplaning

18−2

Jettison:

Emergency

14−2

Limits

4−20

Joint tactical information distribution system

19−19

AN/URC−107

20−8, 20−12

Ice

18−1

On board check

38−36

Identification

Chapter 21

Friend or foe interrogator (AN/APX−76)

21−6

Transponder (AN/APX−100)

21−1

Ignition system, engine

2−30

In chocks, RIO functional checkflight

L or R FUEL LOW light

14−19

procedures

10−32

LAD/CANOPY light

14−30, 14−31

Index−5

CHANGE 2

NAVAIR 01−F14AAD−1

Page

No.

Landing

7−24

Manual bailout

16−6

Carrier pattern (VFR)

8−7

Manual man/seat separation

16−7

Checklist

7−26

Master test panel checks

38−1

Cold−weather operations

18−6

Master test switch operation

38−3

Emergencies

Chapter 15

Maximum airspeeds

4−5

Flaps, slats, and direct lift control

11−2

Meatball contact

8−12

Gross weight limits

4−18

Medium and high−subsonic airspeed

11−5

Hot weather and desert operations

18−6

MFT procedures evaluation

39−2

On wet runway

18−4

Minimum flightcrew requirements

5−5

Preparation, parachute

16−9

Minimum ground training syllabus

5−1

RIO functional checkflight procedures

10−32

Miscellaneous equipment

2−283

With aft hung ordnance

15−17

Mission commander

5−4, 37−1

Landing configuration flight characteristics

11−21

Mission computer system

2−77, 20−5

With aft cg

11−38

Mission evaluation

39−3

Landing gear:

Mission planning and briefing

39−3

Emergencies

15−6

Motive flow fuel pump

2−21

Emergency lowering

15−6

Movable surfaces, inspection of

7−2

Handle

2−132

Multifunction display(s)

2−174

Malfunctions

15−8

Engine caution legends

2−38

Normal operation

2−135

Formats

2−176

Systems

2−132

Reconnaissance data status format

22−9

Lateral control

2−102

Multistatus indicator

2−170

Reversal

11−7

Mutual interference

19−1

Lateral−stick−induced departures

11−13

Launch:

Bar

2−145

Carrier−based procedures

8−1

Gross weight limits

4−18

Limits

4−19

NATOPS evaluation

Part X

Single−engine failure field/catapult

13−2

Program

39−1

Leak(s)

7−2

Qualification and currency requirements

5−3

Detection, environmental control system

2−29

Question bank

39−4

Lighting system

2−265

Navigation

Chapter 20

Lights, approach

2−251

Command and control grid

Chapter 23

Limitations

4−1

Navigation data:

Lineal coverage

22−22

Display

20−12

Long−field arrestment

15−18

Emergency procedures

14−1

Long−range oblique photography camera

Initialization

20−6

(KS−153A with 610−mm lens)

22−24

Navigation system

20−1

Longitudinal control

2−97

Data distribution

20−12

Low brake accumulator pressure

14−35

Operation

20−20

Low subsonic airspeed

11−6

NAVRIT

40−1

Negative angle−of−attack departures

11−20

Night field carrier landing practice

7−37

Night flying

8−12

No−flaps and no−slats landing

15−10

Nomenclature, electronic

1−2, 1−5

Main landing gear

2−133

Normal electrical operation

2−59

Malfunction procedures

39−3

Normal procedures

Part III

Maneuvering:

Normal stalls

11−22

Flaps and slats

11−2, 11−7

Nose landing gear

2−133

Limits

4−10

Nose radome

2−283

Stick force

11−2

Nose strut keel

2−143

Maneuvers, prohibited

4−10

Nosegear catapult system

2−143

Manual approach technique

8−7

Nosewheel steering system

2−141

ORIGINAL

Index−6

ąNAVAIR 01−F14AAD−1

Page

No.

Postflight:

Procedures

39−3

RIO functional checkflight procedures

10−32

OA−8697 V/UHF automatic direction finder

19−18

Postlanding:

OBOGS light

14−29

Pilot

7−27

Oil:

RIO

7−34

Cooling

2−35

Poststart:

Pressure indicators

2−35

Carrier−based procedures

8−1

OIL HOT caution lights

2−35

Night flying

8−12

Oil system:

Pilot

7−13

Engine

2−34

Pilot functional checkflight procedures

10−6

Malfunction

14−17

RIO

7−29

On−board checkout

38−3

On−board oxygen generating system

2−157

RIO functional checkflight procedures

10−27

Power supply system:

On−deck emergencies

12−1

Electrical

2−59

Open−book examination, NATOPS

39−2

Hydraulic

2−69

Operating criteria

5−2

Pneumatic

2−77

Operating limitations

Chapter 4

Preflight:

Operational deployable squadrons

39−3

And line operations

39−3

Oral examination, NATOPS

39−2

Briefing

6−1

Outboard spoiler module:

Carrier−based procedures

8−1

Failure

11−27

Cold−weather operations

18−5

Malfunction

14−44

Night flying

8−12

Outboard spoiler system

2−73

Preland

7−23

Overspeed, engine

14−12

Pressurization

2−152

Oxygen system

2−157

Prestart:

Failure

14−29

Pilot

7−10

Pilot functional checkflight procedures

10−2

RIO

7−29

RIO functional checkflight procedures

10−27

Primary flight controls

11−1

Panels, security of

7−2

Programmable tactical information display

20−6

Panoramic camera

22−2, 22−23

Prohibited maneuvers

4−10

Parachute:

Publications, applicable

39−4

Landing preparation

16−9

PUMP phase circuit breakers popped

14−28

Steering

16−9

Parade formation

9−2

Parking brake

2−140

Pattern entry

7−24

Photographic film

22−26

Pilot tone volume/TACAN command panel

19−7

Question bank, NATOPS

39−4

Pilot:

Procedures

7−8

Reconnaissance operation

22−21

Relief and guidance modes

2−126

Responsibilities

37−1

Pitch:

Radar:

Control

11−1

Altimeter system, AN/APN−194(V)

2−250

SAS degrade

14−38

Beacon (AN/APN−154)

17−2

SAS light

14−38

Radiation areas

3−8

Pitot−static system

2−160

System built−in test

38−47

Failures

14−1

Radar intercept officer:

Planning, mission

39−3

Procedures

7−28

Platform

8−10

Responsibilities

37−1

Pneumatic power supply systems

2−77

Raft boarding

16−9

Pneumatic systems servicing data

3−8

Rain

18−1

Index−7

ORIGINAL

NAVAIR 01−F14AAD−1

Page

No.

Reconnaissance:

Single−engine landing:

Displays and formats

22−9

Operation fuel transfer/feed

2−54

Fault/problem reporting

22−9

Primary mode

15−1

Steering selection

22−11

SEC mode

15−3

Reconnaissance system

22−1

Six−mile DME fix

8−10

Operation

22−13

Slats, maneuvering

11−7

Records and reports

39−3

Special consideration

37−4

Recovery, stall

11−22

Special procedures

Chapter 9

Refueling:

Specific responsibilities, aircrew

37−1

Ground

3−1

Speedbrakes

2−95, 11−2

Hot

2−58

Spin:

In−flight

2−57

Flat

11−20

Requirements for various flight phases

5−4

Inverted

11−21

Reverted rubber skids

18−3

Spoiler:

Roll:

Control

2−105

Control

11−1

Malfunction

14−42

DGR light

14−39

Stability augmentation

11−1

Performance

11−3

Transients

14−40

Response

11−3

Stability augmentation system

2−110, 11−1

SAS degrade

14−39

DFCS

11−6

SAS failure

14−39

Limits

4−13

Uncommanded

14−37

Off

11−27

Rolling limits

4−10

Stability, wing−sweep effects on

11−38

Rpm decay, uncommanded SEC mode

14−13

Stall(s):

Rudder authority failure

14−40

Characteristics

11−9

Rudder−induced departures

11−13

Compressor

14−5

Runup, flight evaluation

39−3

Normal

11−22

Recovery

11−22

Vertical

11−9

Warning, engine

2−38

Standard attitude heading reference system

Search and rescue

37−4

(AN/USN−2(V))

20−5

Seat:

Standard central air data computer

2−79, 20−6

Ejection

2−258

Standby airspeed indicator

2−250

Operation after ejection

2−265

Standby altimeter

2−250

Secondary flight controls

11−2

Standby attitude indicator

2−248

Security of panels

7−2

Start:

Self−test, engine instrument group

2−37

Abnormal

12−1

Sensor capabilites and limitations

22−22

Carrier−based procedures

8−1

SENSOR COND light illuminated

14−28

Crossbleed

2−34

Serial frame camera

22−2, 22−22

Pilot functional checkflight procedures

10−2

Servicing

Chapter 3

START VALVE light, engine

14−12

Shimmy damping

2−143

After engine start

12−1

Shipboard procedures

9−4

Starter limits

4−1

Shore−based procedures checklists

7−1

Static longitudinal stability

11−2

Short−field arrestment

15−18

Store(s)

11−6

Sideslip limits

4−10

Effects on cg location

11−38

Signals:

Management system/jettison

2−278

Audio warning

19−5

Stores loading:

Flightcrew attention

14−1

Authorized

4−21

Ground handling

19−27

Clean and symmetric

4−13

Single−engine failure field/catapult

Stuck/jammed throttle(s)

14−15

launch/waveoff

13−2

Surface condition

7−2

Single−engine flight characteristics

14−11

Surface subsystems

17−8

ORIGINAL

Index−8

ąNAVAIR 01−F14AAD−1

Page

No.

Survival kit deployment

16−7

Towing turn radii and ground clearances

3−15

Survival/postejection procedures

16−6

Training:

Symbology

2−176

Aircrew coordination

37−4

HUD/VDI

22−13

Evaluation squadrons

39−3

Systems

Chapter 2

TRANS/RECT light

14−22

Test and system power ground panel

2−283

Transfer, fuel

2−50

Trim characteristics

11−4

TSEC/KY−58 UHF voice security equipment

19−19

Turbulence

18−4

Turn radii, towing

3−15

Twenty thousand foot checks:

Tactical air navigation system

Pilot functional checkflight procedures

10−22

(AN/ARN−118)

20−8, 22−1

RIO functional checkflight procedures

10−29

Tactical air reconnaissance pod system

22−1

Checklist

7−1

Degraded mode procedures

7−33

Environmental control system

22−2

Limitations

4−21

UHF automatic direction finder

20−11

Subsystem

Chapter 22

UHF voice security equipment (TSEC/KY−58)

19−19

Tactical Imaging Set

40−1

Uncommanded dump

14−19

Takeoff

7−20

Uncommanded engine acceleration:

Aborted

7−22, 13−1

Airborne (no throttle movement)

14−15

And landing flap/slat transition limits

4−13

On deck

12−1

Blown tire during

13−3

Uncommanded roll and/or yaw

14−37

Checklist

7−22

Uncommanded SEC mode rpm decay

14−13

Cold−weather operations

18−5

Unscheduled wing sweep

14−47

Emergencies

Chapter 13

Upright departure

14−49

Gross weight limits

4−18

Recovery

11−15

Hot weather and desert operations

18−6

Pilot functional checkflight procedures

10−14

RIO functional checkflight procedures

10−28

Takeoff configuration flight characteristics

11−21

With aft cg

11−38

Variable exhaust nozzle

2−16

TARPS ECS light illuminate

14−27

Ventilation, engine compartment

2−30

Taxi:

Vertical display indicator symbology

22−13

Flight evaluation

39−3

Vertical recovery

14−49

Night flying

8−12

Vertical stalls

11−9

Pilot

7−20

Viscous hydroplaning

18−3

Pilot functional checkflight procedures

10−13

Voltage monitoring

2−125

RIO

7−32

V/UHF automatic direction finder (OA−8697)

19−18

RIO functional checkflight procedures

10−28

V/UHF radio (AN/ARC−182)

19−7

Taxiing

7−18, 8−4

Carrier−based procedures

8−4

Cold−weather operations

18−5

Hot−weather and desert operations

18−6

Technical directives

1−2

Waiving of minimum ground training

Temperature warning, engine

2−38

requirements

5−1

Ten thousand foot check, pilot functional

Warning light

2−269

checkflight procedures

10−15

Waveoff

8−9, 8−12

Ten−mile DME fix

8−10

Single−engine failure field/catapult launch

13−2

Test prerequisites/restrictions

38−9

Technique

8−9

Throttles

2−23

Weapon systems

Part VIII

Stuck/jammed

14−15

Procedures evaluation

39−2

Thunderstorms

18−4

Weight, aircraft

1−1

Tiedown points

3−15

Weight on−off wheels switch malfunction

12−2, 14−48

Total electrical failure

14−24

Wheel antirotation

2−141

Index−9

ORIGINAL

NAVAIR 01-F14AAD-1

LIST OF EFFECTIVE PAGES

Effective Pages

Page Numbers

Effective Pages

Page Numbers

Change 2

(Reverse Blank)

Original

2-137 thru 2-139

Original

(Reverse Blank)

Change 1

2-140

Change 2

(Reverse Blank)

Change 2

2-141

Change 1

(Reverse Blank)

Original

2-142 thru 2-148

Original

(Reverse Blank)

Change 1

2-149

Original

11 thru 14

Original

2-150

Change 1

2-151

Original

16 thru 22

Original

2-152 thru 2-164

Change 2

Change 1

2-165

Original

24 thru 27

Original

2-166, 2-167

Change 1

28, 29

Change 1

2-168

Original

2-169 thru 2-221

Change 1

31, 32

Change 2

2-222

Original

33, 34

Original

2-223 thru 2-242

Change 1

2-243

Original

36 thru 40

Original

2-244 thru 2-249

Original

41, 42

Change 1

2-250, 2-251

Change 1

43, 44

Original

2-252 thru 2-255

Original

Change 1

2-256, 2-256a (Reverse Blank)

Change 1

46, 47

Original

2-257 thru 2-262

Original

48 thru 50

Change 1

2-263

Original

51 thru 54

Original

2-264 thru 2-268

Original

(Reverse Blank)

Change 1

2-269

Original

1-1 thru 1-5 (Reverse Blank)

Change 2

2-270, 2-271

Original

2-1 thru 2-26

Original

2-272 thru 2-280

Change 1

2-27

Change 1

2-281, 2-282

Original

2-28 thru 2-45

Original

2-283 thru 2-284

Change 2

2-46

Original

3-1 thru 3-19 (Reverse Blank)

Original

2-47

Change 1

4-1

Change 2

2-48

Original

4-2 thru 4-19

Original

2-49 thru 2-51

Change 1

4-20

Change 1

2-52

Original

4-21 (Reverse Blank)

Original

2-53 thru 2-57

Original

(Reverse Blank)

Change 1

2-58

Original

5-1

Original

2-59 thru 2-60

Change 2

5-2

Change 2

2-61

Original

5-3 thru 5-5 (Reverse Blank)

Change 1

2-62

Original

(Reverse Blank)

Original

2-63

Original

6-1 thru 6-4

Change 1

2-64

Original

7-1 thru 7-16

Original

2-65 thru 2-77

Change 2

7-17

Change 1

2-78, 2-78a (Reverse Blank)

Original

7-18 thru 7-20

Original

2-79 thru 2-120

Change 1

7-21

Change 1

2-121 thru 2-124

Original

7-22

Original

2-125 thru 2-131

Change 2

7-23

Change 1

2-132

Change 1

7-24

Original

2-133

Original

7-25 thru 7-28

Change 1

2-134

Change 1

7-29

Original

2-135

Original

7-30

Change 1

2-136

Change 1

7-31

LEP-1

CHANGE 2

NAVAIR 01-F14AAD-1

Effective Pages

Page Numbers

Effective Pages

Page Numbers

Original

7-32 thru 7-38

Original

(Reverse Blank)

Original

8-1 thru 8-13 (Reverse Blank)

Original

19-1 thru 19-17

Original

9-1 thru 9-6

Change 1

19-18

Change 1

9-7 (Reverse Blank)

Original

19-19 thru 19-31 (Reverse Blank)

Original

10-1 thru 10-5

Original

20-1 thru 20-4

Change 2

10-6

Change 1

20-5

Original

10-7 thru 10-30

Original

20-6 thru 20-50

Change 1

10-31

Change 1

20-51 thru 20-52b (Reverse Blank)

Original

10-32

Original

20-53 thru 20-105 (Reverse Blank)

Original

(Reverse Blank)

Original

21-1 thru 21-8

Original

11-1 thru 11-8

Change 1

(Reverse Blank)

Change 2

11-9 thru 11-10a (Reverse Blank)

Original

22-1 thru 22-26

Original

11-11 thru 11-38

Original

23-1 thru 23-5 (Reverse Blank)

Original

63, 64

Original

(Reverse Blank)

Change 2

Original

37-1 thru 37-5 (Reverse Blank)

Original

66 thru 68

Original

38-1 thru 38-72

Change 2

Original

(Reverse Blank)

Original

70 thru 84

Original

39-1 thru 39-14

Change 2

12-1

Change 1

39-15

Original

12-2 thru 12-5 (Reverse Blank)

Original

39-16 thru 39-18

Original

13-1 thru 13-3 (Reverse Blank)

Original

(Reverse Blank)

Change 1

14-1

Original

40-1 thru 40-3

Original

14-2 thru 14-9

Change 1

40-4

Change 2

14-10, 14-11

Original

40-5, 40-6

Original

14-12 thru 14-16

Change 1

40-7, 40-8

Change 2

14-17 thru 14-20a (Reverse Blank)

Original

40-9 thru 40-12

Original

14-21 thru 14-30

Change 1

40-13

Change 1

14-31

Original

40-14 thru 40-19 (Reverse Blank)

Original

14-32 thru 14-41

Original

Index-1

Change 1

14-42, 14-43

Change 1

Index-2

Original

14-44 thru 14-48

Change 2

Index-3 thru Index-5

Change 2

14-49, 14-50

Original

Index-6 thru Index-10

Original

15-1 thru 15-8

Original

FO-1 (Reverse Blank)

Change 1

15-9, 15-10

Original

FO-2 (Reverse Blank)

Original

15-11, 15-12

Change 1

FO-3 (Reverse Blank)

Change 1

15-13

Change 1

FO-4 (Reverse Blank)

Original

15-14

Original

FO-5 (Reverse Blank)

Change 1

15-15

Original

FO-7 (Reverse Blank)

Original

15-16

Original

FO-8 (Reverse Blank)

Change 1

15-17

Original

FO-9 (Reverse Blank)

Original

15-18 thru 15-20

Original

FO-10 (Reverse Blank)

Change 1

15-21 (Reverse Blank)

Original

FO-11 (Reverse Blank)

Original

16-1 thru 16-4

Original

FO-12 (Reverse Blank)

Change 1

16-5, 16-6

Original

FO-13 (Reverse Blank)

Original

16-7 thru 16-9 (Reverse Blank)

Original

FO-14 (Reverse Blank)

Original

(Reverse Blank)

Original

FO-15 (Reverse Blank)

Original

17-1 thru 17-7

Original

FO-16 (Reverse Blank)

Change 2

17-8

Original

FO-17 (Reverse Blank)

Original

17-9 thru 17-14

Change 2

LEP-1, LEP-2

Original

18-1 thru 18-6

CHANGE 2

LEP-2

CIRCUIT BREAKERS

REFERENCE DATA

BINGO

ECS LEAKS

EMERGENCY PROCEDURE TABS

COCKPIT/OXYGEN

ECS

COOLANT/CANOPY

NAVAIR 01-F14AAP-1B

CONTROLLED

NATOPS

EJECT/

MANUAL

EGRESS

POCKET CHECKLIST

GROUND EGRESS

GENERATOR

TRANS/RECT

ELECTRICAL

F-14B

WOW

AIRCRAFT

AICS/AIRSTART

NOZZLE/START VALVE

ENGINE

OIL/THROTTLE

INFLIGHT

ON DECK

FIRE

ELECTRICAL

DISTRIBUTION STATEMENT C — DISTRIBUTION

AUTHORIZED TO U.S. GOVERNMENT AGENCIES

FLAPS

AND THEIR CONTRACTORS (1 JUNE 1992).

SPOILERS

FLIGHT

WINGSWEEP

CONTROL

SAS

DESTRUCTION NOTICE — FOR UNCLASSIFIED,

DUMP

LIMITED DOCUMENTS, DESTROY BY ANY

LEAK

METHOD THAT WILL PREVENT DISCLOSURE OF

FUEL

CONTENTS OR RECONSTRUCTION OF THE

PRESSURE

DOCUMENT.

TRANSFER

COMBINED

FLIGHT

HYDRAULICS

BRAKES

ISSUED BY AUTHORITY OF THE CHIEF OF

NAVAL OPERATIONS AND UNDER THE

DIRECTION OF THE COMMANDER,

ARRESTMENT

NAVAL AIR SYSTEMS COMMAND.

BRAKES

LANDING GEAR/

BLOWN TIRE

LANDING

LAUNCH BAR

TAKEOFF

01 AUGUST 2001

LANDING

SINGLE ENGINE

CRUISE/FUEL

OPS

MIGRATION

ABORT

TAKEOFF

BLOWN TIRE

F-14D. FLIGHT MANUAL (2004) - page 15